Interference correction method and system for arc rail far-field support of half-curved knife device

Abstract

The invention provides an interference correction method and system for a far-field support of an arc rail of a half-curved knife device, and relates to the field of wind tunnel test data processing, and the method comprises the steps: taking the arc rail as a finite-length arc section curve source around the rotating center of the half-curved knife device, and constructing a mathematical model through a basic formula of the induced velocity of a curve source micro-section to a model region; configuring characteristic parameters of the mathematical model; according to the characteristic parameters, calculating the actual wind speed and the airflow deflection angle after the model point is disturbed by the point source; carrying out aerodynamic characteristic correction according to the actual wind speed and the airflow deflection angle; the aerodynamic characteristics include velocity pressure, airflow deflection angle parameters, axial static pressure gradient and component additional influence. According to the invention, interference correction can be carried out on the arc rail far-field support of the half-curved knife device, so that the accuracy of test data is further improved.

Description

Technical Field

[0001] This application relates to the field of wind tunnel test data processing, and in particular to a method and system for interference correction of the far-field support of the arc track of a semi-curved device. Background Technology

[0002] The presence of support devices on wind tunnel test models (except for magnetic levitation) can affect the flow field on and near the model surface, thus interfering with the measured aerodynamic data. Some measurements may even deviate significantly from the actual results. The accuracy of test data is crucial for the accurate assessment of aircraft flight and handling performance and for flight test safety. To pursue higher performance indicators and reduce the development risks of aircraft at various stages, it is necessary to reliably predict the aerodynamic characteristics of aircraft in wind tunnel tests. Support interference is an important component of the interference in the wind tunnel test environment. To this end, researchers at home and abroad have conducted extensive research on the problem of support interference in wind tunnel tests and have established a large number of support interference correction methods for different support devices.

[0003] Some low-speed wind tunnels with a diameter of 4 meters, both domestically and internationally, are equipped with high angle-of-attack devices featuring curved tracks (such as the ONERA-F1 from France, and the FL-9, FL-17, and FL-51 from China). These devices are widely used in high angle-of-attack tail support tests on models. Typically, the tail support rod portion of such devices is defined as the near-field support, while the curved track portion is defined as the far-field support. The interference from the near-field support rod is usually not deducted, while the far-field support with curved tracks typically generates significant velocity-pressure and airflow deflection interference in the model region, which cannot be simply ignored. However, deducting this interference through simulated curved tracks is extremely inconvenient, resulting in most wind tunnels currently not correcting for the interference from the semi-vertical far-field support. Summary of the Invention

[0004] The purpose of this application is to provide a method, system, computer-readable storage medium, electronic device, and computer program product for interference correction of the far-field support of the arc rail of a semi-curved device, which can correct interference of the far-field support of the arc rail of the semi-curved device during the test, thereby further improving the accuracy of the test data and achieving practical engineering results.

[0005] To address the aforementioned technical problems, this application provides an interference correction method for the far-field support of the arc track of a semi-curved cutter device. The specific technical solution is as follows:

[0006] The arc track is regarded as a finite-length arc curve source around the center of rotation of the semi-curved knife device, and a mathematical model is constructed based on the basic formula of the induced velocity of the micro-segment of the curve source on the model area.

[0007] Configure the feature parameters of the mathematical model;

[0008] Calculate the actual wind speed and airflow deflection angle of the model point after it is disturbed by a point source based on the aforementioned characteristic parameters;

[0009] According to the actual wind speed and the airflow deflection angle, aerodynamic characteristics are corrected; the aerodynamic characteristics include speed pressure, airflow deflection angle parameters, axial static pressure gradient and component additional influence.

[0010] Optionally, the arc track is regarded as a limited length arc segment curve source around the rotation center of the half-bent knife device, and a mathematical model is constructed by using the induced velocity basic formula of the curve source micro segment to the model area.

[0011] Based on the low-speed incompressible linearized potential flow theory, the arc track in the wind tunnel is regarded as a limited length arc segment curve source around the rotation center of the half-bent knife device, and the projection of the curve source micro segment in the vertical direction and the straight cloud inflow flow in the wind tunnel are regarded as a cylindrical flow, and an integral form of the induced velocity formula of the limited length arc segment curve source to the model area is established by using the induced velocity basic formula of the curve source micro segment to the model area, and the mathematical model is obtained.

[0012] Optionally, the characteristic parameters of the mathematical model include:

[0013] According to the arc track characteristics of different wind tunnel half-bent knife devices, the maximum thickness of the arc track, the arc track wake reduction coefficient, the height of the wind tunnel and the distance from the rotation center of the half-bent knife device to the arc track are set;

[0014] According to different model position parameters, the distance of the projection of the component half-component average aerodynamic chord 1 / 2 chord point on the longitudinal symmetry plane relative to the arc track is set;

[0015] According to the distance and the preset pitch angle, the coordinates of the component point relative to the point source are calculated;

[0016] According to the cantilever equivalent radius and the inflow velocity, the point source intensity is calculated;

[0017] The aircraft body volume, the aircraft body length, the flat tail normal force slope, the vertical tail lateral force slope, the X coordinate of the flat tail average aerodynamic chord 1 / 2 chord point relative to the moment reference point, the X coordinate of the vertical tail average aerodynamic chord 1 / 2 chord point relative to the moment reference point and the Y coordinate of the vertical tail average aerodynamic chord 1 / 2 chord point relative to the moment reference point are set.

[0018] Optionally, according to the characteristic parameters, the actual wind speed and the airflow deflection angle of the model point after being disturbed by the point source are calculated.

[0019] The induced velocity of the limited length arc segment curve source to the model point is calculated.

[0020] According to the induced velocity, the actual wind speed and the actual airflow deflection angle of the component point after being disturbed by the point source are calculated.

[0021] Optionally, according to the actual wind speed and the airflow deflection angle, aerodynamic characteristics are corrected.

[0022] According to the actual wind speed, the model speed pressure in the speed pressure and the aerodynamic force coefficient are corrected;

[0023] According to the actual airflow deflection angle, the model angle of attack and the sideslip angle in the airflow deflection angle parameter are corrected;

[0024] According to the actual wind speed after the disturbance at the point where the nose is located and the actual wind after the disturbance at the point where the tail is located, the model axial force coefficient is corrected;

[0025] According to the actual airflow deflection angle, the average aerodynamic chord length of the wing and the wing span, the normal force coefficient, the pitching moment coefficient, the lateral force coefficient and the yawing moment coefficient in the component additional influence are corrected.

[0026] Optionally, after the aerodynamic characteristic correction according to the actual wind speed and the airflow deflection angle, the method further comprises:

[0027] The correction effect verification is performed on the arc rail far field support of the half-bent knife device, and a verification result is obtained;

[0028] According to the verification result, the correction and optimization are performed.

[0029] The application also provides an interference correction system of an arc rail far field support of a half-bent knife device, comprising:

[0030] A model construction module is configured to regard the arc rail as a limited length arc segment curve source around the rotation center of the half-bent knife device, and construct a mathematical model by using the induced velocity basic formula of the curve source micro segment to the model area;

[0031] A characteristic parameter calculation module is configured to configure the characteristic parameters of the mathematical model;

[0032] An actual parameter calculation module is configured to calculate the actual wind speed and the airflow deflection angle after the disturbance of the model point by the point source according to the characteristic parameters;

[0033] An interference correction module is configured to correct the aerodynamic characteristics according to the actual wind speed and the airflow deflection angle; the aerodynamic characteristics include the speed pressure, the airflow deflection angle parameter, the axial static pressure gradient and the component additional influence.

[0034] The application also provides a computer readable storage medium, which stores a computer program; when the computer program is executed by a processor, the steps of the method described above are implemented.

[0035] The application also provides an electronic device, which comprises a memory and a processor; the memory stores a computer program; when the processor invokes the computer program in the memory, the steps of the method described above are implemented.

[0036] The application also provides a computer program product, which comprises a computer program; when the computer program is executed, the steps of the method described above are implemented.

[0037] The application provides a semi-curved knife device arc rail far field support interference correction method, comprising the following steps: regarding the arc rail as a limited length arc segment curve source around the semi-curved knife device rotation center, constructing a mathematical model according to a basic formula of induced velocity of a model area by a curve source micro segment; configuring characteristic parameters of the mathematical model; calculating actual wind speed and airflow deflection angle of a model point after the model point is disturbed by a point source according to the characteristic parameters; and correcting aerodynamic characteristics according to the actual wind speed and the airflow deflection angle; the aerodynamic characteristics include speed pressure, airflow deflection angle parameters, axial static pressure gradient and component additional influence.

[0038] By introducing curve source micro segment integration, the application can accurately capture the non-uniform three-dimensional disturbance field generated by the semi-curved knife-arc rail combination in the model area, so that the correction amount of key parameters such as axial static pressure gradient, speed pressure and airflow deflection angle is highly consistent with the real flow field, the aerodynamic coefficient error caused by support interference can be effectively reduced, and the measurement accuracy of lift-drag ratio, moment and pressure distribution can be effectively improved. By explicitly modeling the component additional influence, the scale effect error caused by the traditional "equivalent block" assumption is avoided, and the data reliability under non-linear working conditions such as transonic speed and large angle of attack is obviously improved; the overall algorithm only depends on the geometry and incoming flow parameters, does not require additional sensors or pressure holes, and does not require modification of existing wind tunnel facilities, has the advantages of strong engineering portability and low implementation risk, and can be directly applied to fine wind tunnel test of complex layouts such as hypersonic aircraft and large wing span unmanned aerial vehicles, thereby providing high-fidelity data support for subsequent numerical verification and model design.

[0039] The application also provides a semi-curved knife device arc rail far field support interference correction system, a computer readable storage medium, an electronic device and a computer program product, which have the above beneficial effects, and details are not repeated here. BRIEF DESCRIPTION OF DRAWINGS

[0040] In order to more clearly illustrate the technical solutions in the embodiments of the application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description only constitute the embodiments of the application, and for those skilled in the art, other drawings can be obtained without creative labor on the basis of the provided drawings.

[0041] Figure 1 A flowchart of a semi-curved knife device arc rail far field support interference correction method provided by the embodiments of the application is provided.

[0042] Figure 2 A cylinder flow viscosity separation flow diagram provided by the embodiments of the application is provided.

[0043] Figure 3A FL-17 wind tunnel semi-bent knife device arc track far field interference correction effect schematic diagram provided by the embodiment of the application is shown in FIG. 1.

[0044] Figure 4 A FL-17 wind tunnel semi-bent knife device arc track far field interference effect schematic diagram provided by the embodiment of the application is shown in FIG. 1.

[0045] Figure 5 A semi-bent knife device arc track far field support interference correction system structure schematic diagram provided by the embodiment of the application is shown in FIG. 2.

[0046] Figure 6 A structure diagram of an electronic device provided by the embodiment of the application is shown in FIG. 3. DETAILED DESCRIPTION

[0047] To make the objectives, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are some embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0048] The purpose of the present application is to be able to correct the semi-column interference in real time during the test, so as to further improve the test data accuracy and achieve the effect of engineering practice.

[0049] Reference is made to Figure 1 , Figure 1 A flowchart of a semi-bent knife device arc track far field support interference correction method provided by the embodiment of the present application is shown in FIG. 1, and the method comprises the following steps.

[0050] S101: The arc track is regarded as a limited length arc segment curve source around the semi-bent knife device rotation center, and a mathematical model is constructed by using a basic formula of induced velocity of a curve source microsegment to a model area;

[0051] S102: Feature parameters of the mathematical model are configured;

[0052] S103: Actual wind speed and airflow deflection angle of a model point after disturbance of a point source are calculated according to the feature parameters;

[0053] S104: Aerodynamic characteristics are corrected according to the actual wind speed and the airflow deflection angle; the aerodynamic characteristics include speed pressure, airflow deflection angle parameter, axial static pressure gradient and component additional influence.

[0054] In step S101, the mathematical model is established (defined according to a commonly used coordinate system of computational aerodynamics, X axis along airflow direction, Y axis upward, and Z axis direction consistent with right-hand system).

[0055] Specifically, based on the theory of low-speed inviscid incompressible linearized potential flow, the arc track inside the wind tunnel is regarded as a finite-length circular arc curve source around the rotation center of the semi-curved device. The rotation center of the semi-curved device is considered to coincide with the center of the circular arc segment of the arc track. The projection of the curve source micro-segment in the vertical direction and the flow of the wind tunnel straight cloud are regarded as the flow around a cylinder. The basic formula of the induced velocity of the curve source micro-segment on the model area is used to establish the integral form of the induced velocity formula of the finite-length circular arc curve source on the model area, thus obtaining the mathematical model.

[0056] See Figure 2 , Figure 2 The formula for calculating the induced velocity of the point source in the model region, based on the viscous separation flow diagram provided in this embodiment of the application, is as follows:

[0057] ;

[0058] ;

[0059] ;

[0060] in, This indicates the intensity of the infinitely long straight-line source corresponding to the micro-segment of the curve. Indicates the length of the curve source micro-segment. This represents the angle between the line connecting the model point (or component point) to the curve source micro-segment and the vertical axis. This represents the distance from a model point (or component point) to the curve source micro-segment. This represents the induced velocity component in the x-direction. This represents the induced velocity component in the y-direction. The induced velocity component in the z-direction is represented by A, which is the lower end of the curve source, and B is the upper end of the curve source.

[0061] In step S102, the feature parameters of the mathematical model need to be configured. Specifically, the calculation process of these feature parameters may include the following parameters:

[0062] The equivalent radius of the cantilever is set according to the tail support of the wind tunnel cantilever.

[0063] The distance between the projection of the half-section average aerodynamic chord point of the component and the longitudinal symmetry plane and the arc track is set according to the position parameters of different models.

[0064] Calculate the coordinates of the component point relative to the point source based on the distance and the preset pitch angle;

[0065] Calculate the point source intensity based on the cantilever equivalent radius and the incoming flow velocity;

[0066] Set the body volume, body length, flat tail normal force slope, vertical tail lateral force slope, flat tail average aerodynamic chord 1 / 2 chord point relative moment reference point X coordinate, vertical tail average aerodynamic chord 1 / 2 chord point relative moment reference point X coordinate and vertical tail average aerodynamic chord 1 / 2 chord point relative moment reference point Y coordinate.

[0067] Specifically, for different wind tunnel semi-curved knife device arc track characteristics, D, k0, H, Wherein, D represents the maximum thickness of the arc track, k0 represents the arc track wake reduction coefficient, H represents the height of the wind tunnel, Indicates the distance from the semi-curved knife device rotating core to the arc track (i.e. the radius of the circular arc segment);

[0068] For different model (component) position parameters, set R, wherein R is taken as the distance from the projection of the model / component left (or right) half average aerodynamic chord 1 / 2 chord point on the longitudinal symmetry plane to the arc track;

[0069] The model point (or component point) and the curve source micro-segment geometric relationship is:

[0070] ;

[0071] ;

[0072] Accordingly, the integral result of the calculation formula of the finite length circular arc segment curve source on the model area induced velocity is:

[0073] ;

[0074] ;

[0075] ;

[0076] The calculation Formula is:

[0077] ;

[0078] Wherein, The incoming flow velocity, , The model attack angle and sideslip angle.

[0079] For different model geometric parameters, set , , , , , , And other parameters, wherein, The body volume, The body length,represents the horizontal tail normal force slope, represents the vertical tail lateral force slope, represents the horizontal tail average aerodynamic chord 1 / 2 chord point relative moment reference point X coordinate, represents the horizontal tail average aerodynamic chord 1 / 2 chord point relative moment reference point X coordinate, represents the horizontal tail average aerodynamic chord 1 / 2 chord point relative moment reference point X coordinate, represents the horizontal tail average aerodynamic chord 1 / 2 chord point relative moment reference point Y coordinate, and the calculation formula is , , The formula is: , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , , represents the horizontal tail normal force slope, represents the vertical tail lateral force slope, represents the horizontal tail average aerodynamic chord 1 / 2 chord point relative moment reference point X coordinate, represents the horizontal tail average aerodynamic chord 1 / 2 chord point relative moment reference point X coordinate, represents the horizontal tail average aerodynamic chord 1 / 2 chord point relative moment reference point Y coordinate, and the calculation formula is , The formula is:

[0080] ;

[0081] ;

[0082] wherein, , are respectively the horizontal tail and the vertical tail aspect ratio, , are respectively the horizontal tail and the vertical tail 1 / 2 chord line sweepback angle, , are respectively the horizontal tail and the vertical tail area, is the model reference area.

[0083] In step S103, the actual wind speed and the airflow deflection angle of the model point after being disturbed by the point source need to be calculated according to the characteristic parameters. Specifically, the induced velocity of the finite length circular arc curve source on the model point can be calculated first, and then the actual wind speed and the actual airflow deflection angle of the component point after being disturbed by the point source can be calculated according to the induced velocity.

[0084] Specifically, the induced velocity of the finite length circular arc curve source on the model point (or the component point) is calculated first , , The formula is:

[0085] For the model positive direct tail support case, the calculation formula is:

[0086] ;

[0087] ;

[0088] ;

[0089] For the model reverse direct tail support case, the calculation formula is:

[0090] ;

[0091] ;

[0092] ;

[0093] Then calculate the actual wind speed at the model point (or component point) after being disturbed by a finite-length circular arc source. and actual airflow deflection angle , The formula is:

[0094] ;

[0095] ;

[0096] ;

[0097] In step S104, aerodynamic characteristic correction is performed based on the actual wind speed and the airflow deflection angle, which may specifically include the following steps:

[0098] The model velocity pressure and aerodynamic coefficients in the velocity pressure are corrected based on the actual wind speed;

[0099] The model elevation angle and sideslip angle in the airflow deflection parameters are corrected based on the actual airflow deflection angle.

[0100] The axial force coefficient of the model is corrected based on the actual wind speed at the point where the nose is disturbed and the actual wind speed at the point where the tail is disturbed.

[0101] The normal force coefficient, pitching moment coefficient, lateral force coefficient, and yaw moment coefficient in the additional effects of the components are corrected based on the actual airflow deflection angle, the average aerodynamic chord length of the wing, and the wing span.

[0102] Aerodynamic characteristic correction is implemented (according to the commonly used coordinate system definition in flight mechanics, the X-axis is parallel to the fuselage axis and points forward, the Y-axis is upward, and the Z-axis direction conforms to the right-hand system).

[0103] During velocity-pressure correction, the model velocity-pressure and aerodynamic coefficients are corrected using the actual wind speed at the model points.

[0104] When correcting the airflow deflection angle, the model's angle of attack and sideslip angle are corrected based on the actual airflow deflection angle at the model point;

[0105] When correcting the axial static pressure gradient, the axial force coefficient of the model is corrected by the axial static pressure gradient generated by the difference in actual wind speed between the head and tail points of the model.

[0106] When correcting for additional effects on components, the aerodynamic coefficients of the model are corrected based on the additional force and torque generated by the actual airflow deflection angle at the component point.

[0107] Aerodynamic characteristic correction (according to the commonly used coordinate system definition in flight mechanics, the X-axis is parallel to the fuselage axis and points forward, the Y-axis is upward, and the Z-axis direction conforms to the right-hand system).

[0108] For the speed pressure correction:

[0109] Model speed pressure and aerodynamic coefficients The correction formula is:

[0110] ;

[0111] ;

[0112] where subscript u represents the variable before correction.

[0113] For the flow angle correction:

[0114] Model angle of attack and side slip angle The correction formula is:

[0115] ;

[0116] ;

[0117] For the axial static pressure gradient correction:

[0118] Model axial force coefficient The correction formula is:

[0119] ;

[0120] where, and respectively represent the actual wind speed after disturbance at the points where the nose and tail are located.

[0121] For the component additional influence correction:

[0122] The correction formula for the influence of component additional force and moment on aerodynamic coefficients is:

[0123] ;

[0124] ;

[0125] ;

[0126] ;

[0127] ;

[0128] where, , , , , respectively are normal force coefficient, pitching moment coefficient, lateral force coefficient, yawing moment coefficient, rolling moment coefficient, is the mean aerodynamic chord length of the wing (i.e., the reference chord length), is the wing span (i.e., the reference span).

[0129] The present application can accurately capture the non-uniform three-dimensional disturbance field generated by the semi-curved knife-arc rail combination in the model area by introducing curve source micro-section integration, so that the correction amount of key parameters such as axial static pressure gradient, velocity pressure and airflow deflection angle is highly consistent with the real flow field, which can effectively reduce the aerodynamic coefficient error caused by the support interference, and effectively improve the measurement accuracy of lift-drag ratio, moment and pressure distribution. The present application avoids the scale effect error caused by the traditional "equivalent block" assumption by explicitly modeling the component additional influence, so that the data reliability under non-linear working conditions such as transonic speed and large angle of attack is significantly improved; the overall algorithm only relies on geometry and incoming flow parameters, without the need for additional sensors or pressure holes, and does not require modification of existing wind tunnel facilities, with the advantages of strong engineering portability, low implementation risk, and can be directly applied to fine wind tunnel test of complex layout such as hypersonic aircraft and large wing span unmanned aerial vehicle, providing high-fidelity data support for subsequent numerical verification and model design.

[0130] In a feasible implementation, after the aerodynamic characteristic correction, the arc rail far-field support of the semi-curved knife device can be further corrected and verified to obtain a verification result, and the correction and optimization are performed according to the verification result.

[0131] In a feasible correction effect verification process, a standard model and a semi-curved knife-arc rail support can be installed in a wind tunnel, and original aerodynamic data in a full angle of attack range can be collected according to a test outline; then, under the same model and the same incoming flow condition, a low-interference tail support or a magnetic suspension support is replaced to obtain approximate "no support" reference data, and the difference between the two curves is the current support interference. The same set of geometry and incoming flow parameters are input into the curve source interference correction program that has been constructed, and the predicted correction amount of the velocity pressure, the airflow deflection angle, the axial static pressure gradient and the component additional influence corresponding to each angle of attack is output at one time. The predicted value is superimposed on the original data to obtain the "corrected curve".

[0132] The corrected curve and the reference no-support curve are compared point by point: if the deviations of the lift-drag coefficient, the moment coefficient and the pressure center position all fall within the test error band, it is determined that the verification is passed; if individual angles of attack appear out of tolerance, the curve source model is traced back, the characteristic parameters such as arc segment segmentation density, source intensity distribution and boundary conditions are adjusted, and the calculation is re-performed and compared again until the deviation converges to the allowable range. Finally, the optimized characteristic parameters are solidified as the formal correction template, and verification working conditions under different Reynolds numbers and Mach numbers are supplemented to form a correction database covering the full envelope, and subsequent tests of the same type can directly call the template to complete rapid and high-precision support interference correction.

[0133] See Figure 3 and Figure 4 , Figure 3 This is a schematic diagram illustrating the far-field interference correction effect of the FL-17 wind tunnel semi-curved scissor device provided in the embodiments of this application. Figure 4 This is a schematic diagram of the far-field interference effect of the arc track of the FL-17 wind tunnel semi-curved knife device provided in the embodiments of this application. Figure 3 and Figure 4 In the diagram, the horizontal axis represents the angle of attack. The unit is angle, used to represent the tilt angle of the model relative to the incoming flow direction. The vertical axis represents aerodynamic coefficients, including lift and drag coefficients. FL-17_Closed_Arc represents the measurement results under certain arc-shaped support interference, and FL-17_Closed_Arc_Far represents the measurement results (or corrected results) under conditions far from the arc-shaped support interference. When the two curves differ significantly, it indicates that the arc-shaped support interference is significant and correction is required. When the two curves are close or coincident, it indicates that the aforementioned interference correction method is effective, accurately eliminating the influence of support interference and obtaining aerodynamic data that more closely approximates the actual flow field.

[0134] It is evident that the interference from the long cantilever far-field support of the tail support mechanism in a large low-speed wind tunnel cannot be simply ignored. The engineering correction method presented in this application shows good agreement with experimental and CFD results, indicating that the correction method is reliable. It should be noted that this application does not currently consider the influence of the wind tunnel boundary (tunnel wall) on the interference of the long cantilever far-field support.

[0135] See Figure 5 , Figure 5 This is a schematic diagram of an interference correction system for a far-field support of a semi-curved knife device's arc track, provided in an embodiment of this application. The system includes:

[0136] The model building module is used to treat the arc track as a finite-length arc curve source around the center of rotation of the semi-curved knife device, and to build a mathematical model based on the basic formula of the induced velocity of the curve source micro-segment on the model area.

[0137] The feature parameter calculation module is used to configure the feature parameters of the mathematical model;

[0138] The actual parameter calculation module is used to calculate the actual wind speed and airflow deflection angle of the model point after being disturbed by a point source based on the characteristic parameters.

[0139] The interference correction module is used to correct aerodynamic characteristics based on the actual wind speed and the airflow deflection angle; the aerodynamic characteristics include velocity pressure, airflow deflection angle parameters, axial static pressure gradient, and component-related effects.

[0140] This application also provides an embodiment corresponding to a computer-readable storage medium. The computer-readable storage medium stores a computer program, which, when executed by a processor, implements the steps of the method described in the above method embodiments.

[0141] It is understood that if the methods in the above embodiments are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and executes all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0142] The computer-readable storage medium provided in this embodiment includes the method mentioned above, and has the same effect.

[0143] This application also provides an electronic device, see [link to document]. Figure 6 The present application provides a structural diagram of an electronic device, as shown in the embodiment. Figure 6 As shown, it may include a processor 1410 and a memory 1420.

[0144] The processor 1410 may include one or more processing cores, such as a quad-core processor or an octa-core processor. The processor 1410 may be implemented using at least one hardware form selected from DSP (Digital Signal Processing), FPGA (Field-Programmable Gate Array), and PLA (Programmable Logic Array). The processor 1410 may also include a main processor and a coprocessor. The main processor, also known as a CPU (Central Processing Unit), is used to process data in the wake-up state; the coprocessor is a low-power processor used to process data in the standby state. In some embodiments, the processor 1410 may integrate a GPU (Graphics Processing Unit), which is responsible for rendering and drawing the content to be displayed on the screen. In some embodiments, the processor 1410 may also include an AI (Artificial Intelligence) processor, which is used to handle computational operations related to machine learning.

[0145] The memory 1420 may include one or more computer-readable storage media, which may be non-transitory. The memory 1420 may also include high-speed random access memory and non-volatile memory, such as one or more disk storage devices or flash memory devices. In this embodiment, the memory 1420 is used to store at least the following computer program 1421, which, after being loaded and executed by the processor 1410, is capable of implementing the relevant steps in the methods executed by the electronic device side as disclosed in any of the foregoing embodiments. In addition, the resources stored in the memory 1420 may also include an operating system 1422 and data 1423, etc., and the storage method may be temporary storage or permanent storage. The operating system 1422 may include Windows, Linux, Android, etc.

[0146] In some embodiments, the electronic device may further include a display screen 1430, an input / output interface 1440, a communication interface 1450, a sensor 1460, a power supply 1470, and a communication bus 1480.

[0147] certainly, Figure 6 The structure of the electronic device shown does not constitute a limitation on the electronic device in the embodiments of this application. In practical applications, the electronic device may include more than [other components]. Figure 6 More or fewer components as shown, or combinations of certain components.

[0148] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. As the system provided in the embodiments corresponds to the method provided in the embodiments, the description is relatively simple; relevant parts can be found in the method section.

[0149] This document uses specific examples to illustrate the principles and implementation methods of this application. The descriptions of the above embodiments are only for the purpose of helping to understand the methods and core ideas of this application. It should be noted that those skilled in the art can make several improvements and modifications to this application without departing from the principles of this application, and these improvements and modifications also fall within the protection scope of this application.

[0150] It should also be noted that, in this specification, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

Claims

1. A method for interference correction of a semi-cantilevered device arc rail far field support, characterized in that, The method comprises the following steps: The arc track is regarded as a limited length arc segment curve source around the half-bent knife device rotating center, and a mathematical model is constructed based on the basic formula of the induced velocity of the curve source micro segment to the model area; The characteristic parameters of the mathematical model are configured; The actual wind speed and airflow deflection angle of the model point disturbed by the point source are calculated according to the characteristic parameters; The aerodynamic characteristics are corrected according to the actual wind speed and the airflow deflection angle; the aerodynamic characteristics include speed pressure, airflow deflection angle parameters, axial static pressure gradient and component additional influence.

2. The method of claim 1, wherein, The arc track is regarded as a limited length arc segment curve source around the half-bent knife device rotating center, and a mathematical model is constructed based on the basic formula of the induced velocity of the curve source micro segment to the model area, which comprises the following steps: Based on the low-speed incompressible linear potential flow theory, the arc track in the wind tunnel is regarded as a limited length arc segment curve source around the half-bent knife device rotating center, and the projection of the curve source micro segment in the vertical direction and the straight cloud inflow flow in the wind tunnel are regarded as cylindrical flow, and the integral form of the induced velocity formula of the limited length arc segment curve source to the model area is established based on the basic formula of the induced velocity of the curve source micro segment to the model area, and the mathematical model is obtained.

3. The method of claim 1, wherein, The characteristic parameters of the mathematical model are configured, which comprises the following steps: The maximum thickness of the arc track, the arc track wake reduction coefficient, the height of the wind tunnel and the distance from the half-bent knife device rotating center to the arc track are set according to the arc track characteristics of different wind tunnel half-bent knife devices; The distance of the projection of the component half-component average aerodynamic chord 1 / 2 chord point on the longitudinal symmetry plane relative to the arc track is set according to different model position parameters; The body volume, the body length, the normal force slope of the horizontal tail, the lateral force slope of the vertical tail, the X coordinate of the horizontal tail average aerodynamic chord 1 / 2 chord point relative to the moment reference point, the X coordinate of the vertical tail average aerodynamic chord 1 / 2 chord point relative to the moment reference point and the Y coordinate of the vertical tail average aerodynamic chord 1 / 2 chord point relative to the moment reference point are set.

4. The method of claim 3, wherein, The actual wind speed and airflow deflection angle of the model point disturbed by the point source are calculated according to the characteristic parameters, which comprises the following steps: The induced velocity of the limited length arc segment curve source to the model point is calculated; The actual wind speed and actual airflow deflection angle of the component point disturbed by the point source are calculated according to the induced velocity.

5. The method of claim 4, wherein, The aerodynamic characteristics are corrected according to the actual wind speed and the airflow deflection angle, which comprises the following steps: The model speed pressure and aerodynamic force coefficient in the speed pressure are corrected according to the actual wind speed; The model pitch angle and sideslip angle in the airflow deflection angle parameters are corrected according to the actual airflow deflection angle; The model axial force coefficient is corrected according to the actual wind speed of the nose point and the actual wind of the tail point; The normal force coefficient, the pitching moment coefficient, the lateral force coefficient and the yawing moment coefficient in the component additional influence are corrected according to the actual airflow deflection angle, the wing average aerodynamic chord length and the wing span.

6. The method of claim 1, wherein, After the aerodynamic characteristics are corrected according to the actual wind speed and the airflow deflection angle, the following steps are further included: The correction effect verification is performed on the far-field support of the half-bent knife device arc track, and a verification result is obtained; The correction is optimized according to the verification result.

7. A jam correction system for a semi-cant device arc rail far field support, characterized by, The method comprises the following steps: A model construction module is used to regard the arc track as a limited length arc segment curve source around the half-bent knife device rotating center, and a mathematical model is constructed based on the basic formula of the induced velocity of the curve source micro segment to the model area; A characteristic parameter calculation module is used to configure the characteristic parameters of the mathematical model; An actual parameter calculation module is configured to calculate an actual wind speed and an airflow deflection angle of a point on the model after the point is disturbed by a point source according to the characteristic parameter calculation model; An interference correction module is configured to correct aerodynamic characteristics including speed pressure, airflow deflection angle parameters, axial static pressure gradient and component additional influence according to the actual wind speed and the airflow deflection angle.

8. An electronic device, comprising: The method comprises the following steps: A memory is configured to store a computer program; A processor is configured to execute the computer program to implement the steps of the interference correction method of the semi-cantilevered blade device arc rail far-field support according to any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that, The computer readable storage medium stores a computer program, and the computer program is executed to implement the steps of the interference correction method of the semi-cantilevered blade device arc rail far-field support according to any one of claims 1 to 6.

10. A computer program product, characterised in that, The computer program is executed to implement the steps of the interference correction method of the semi-cantilevered blade device arc rail far-field support according to any one of claims 1 to 6.

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