Active control method, system and medium for wingtip vortex based on surface pressure feedback and synthetic jet

Abstract

This application provides a method, system, and medium for active control of wingtip vortices based on surface pressure feedback and synthetic jets. The method includes: acquiring pressure data in real time based on an array of pressure sensors arranged on the wing surface; performing time-frequency analysis on the pressure data to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics; retrieving flow field characteristics from a pre-analyzed wingtip vortex optimal disturbance mode database to obtain dimensionless information; converting the dimensionless information into the driving frequency, driving voltage, and phase command of the synthetic jet actuator to generate a periodic jet; continuously monitoring the power spectral density and suction peak changes of pressure sensors at specific locations on the wing to determine whether the flow field meets the rapid instability condition; if the rapid instability condition is not met, adjusting the frequency or phase difference of the synthetic jet. This invention can achieve rapid capture and closed-loop control from flow field data to optimal disturbance application, effectively promoting the instability and rapid decay of wingtip vortices.

Description

Technical Field

[0001] This application relates to the fields of aerodynamics and flow control, and more specifically, to a method, system, and medium for active control of wingtip vortices based on surface pressure feedback and synthetic jets. Background Technology

[0002] During flight, aircraft generate strong wingtip vortices at the wingtips. These wake vortices not only produce induced drag, affecting flight economy, but their prolonged lingering behind the runway also poses a safety hazard to subsequent takeoffs and landings (i.e., wake encounter problems). Therefore, accelerating the dissipation and decay of wingtip vortices has always been a research hotspot in the aviation field. Existing control methods are mostly passive or open-loop active control, which struggles to apply the most effective disturbances to the real-time changing flow field environment. To achieve efficient control, an active control technology is needed that can quickly identify and precisely apply optimal disturbance modes based on real-time flow field feedback. Summary of the Invention

[0003] The purpose of this application is to provide a method, system, and medium for active control of wingtip vortices based on surface pressure feedback and synthetic jets, which can achieve rapid capture and closed-loop control from flow field data to optimal disturbance application, effectively promoting the instability and rapid decay of wingtip vortices.

[0004] This application also provides an active control method for wingtip vortex based on surface pressure feedback and synthetic jet, including: Pressure data is collected in real time based on an array of pressure sensors arranged on the wing surface; time-frequency analysis is performed on the pressure data to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics. Based on the pre-solution analysis of the wingtip vortex optimal disturbance mode database, flow field characteristics are retrieved, and the dimensionless frequency, phase distribution, and spatial location information of the optimal external disturbance are matched to obtain dimensionless information. Dimensionless information is converted into driving frequency, driving voltage and phase commands for the synthetic jet actuator to control the actuator to generate a periodic jet that matches the optimal disturbance mode at a specific location; Continuously monitor the power spectral density and suction peak changes of pressure sensors at specific locations on the wing to determine whether the flow field meets the conditions for rapid instability; If the rapid instability condition is not met, the frequency or phase difference of the synthetic jet is adjusted by inverting the optimal disturbance mechanism model until the flow field reaches the preset instability state.

[0005] Optionally, in the active control method of wingtip vortex based on surface pressure feedback and synthetic jet described in the embodiments of this application, a high-bandwidth pressure sensor array is arranged on the upper and lower surfaces of the wingtip and near-wingtip region. The sensors are distributed along the chord and spanwise directions, and the spacing between adjacent sensors is set to 6~12mm; Real-time acquisition of unsteady pressure coefficients on the wing surface; comparison of time-averaged pressure values ​​at various points in the array based on the wingtip suction peak positioning principle. The key location is obtained by identifying the sensor position with the lowest average pressure, which corresponds to the projection of the wingtip vortex core onto the wing surface. Real-time Fast Fourier Transform (FFT) and bandpass filtering were performed on the pressure time-series signals from the key location and surrounding sensors to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics.

[0006] Optionally, in the active control method for wingtip vortex based on surface pressure feedback and synthetic jet described in the embodiments of this application, based on the wingtip vortex optimal disturbance mode database of pre-solution analysis, flow field characteristics are retrieved, and the dimensionless frequency, phase distribution, and spatial location information of the optimal external disturbance are matched to obtain dimensionless information, specifically including: Based on high-precision numerical simulation or wind tunnel experiments, a pre-solution analysis database is established for the target airfoil under different Reynolds numbers and angles of attack, storing the flow field response characteristics and optimal disturbance parameters corresponding to each working condition; Based on the pressure data, the Reynolds number, angle of attack, and wingtip vortex shedding frequency under the current operating conditions are extracted to obtain the real-time flow field characteristics; The real-time flow field characteristics are input into a pre-built database, and interpolation retrieval is performed to locate the pre-solution operator under the corresponding working condition. Solve the singular value decomposition of the retrieved pre-formula operator to obtain the right singular vector corresponding to the maximum singular value, and obtain the dimensionless frequency, phase distribution and spatial location information of the optimal external perturbation.

[0007] Optionally, in the active wingtip vortex control method based on surface pressure feedback and synthetic jet described in the embodiments of this application, the driving frequency of the synthetic jet is... The calculation formula is as follows: in, For the incoming flow velocity, The average aerodynamic chord length; This represents the dimensionless Strauhal number.

[0008] Optionally, in the active control method for wingtip vortex based on surface pressure feedback and synthetic jet described in the embodiments of this application, the pre-solution operator The transfer function relationship between the external forced input and the flow response output in the linearized Navier-Stokes (NS) equations is described by the following formula: in, It is a state vector (velocity, pressure fluctuation). This is due to the external disturbance (i.e., the effect of the synthetic jet). To linearize the Navier-Stokes operator, singular value decomposition (SVD) is performed on the predicate operator, as shown in the following formula: The corresponding right singular vector This is the optimal perturbation mode. Represents the maximum singular value. The singular values ​​obtained from the decomposition, These are the left and right singular vectors obtained from the decomposition, respectively. The maximum value among the singular values ​​is represented as... The corresponding right singular vector This is the optimal perturbation mode.

[0009] Optionally, in the active control method for wingtip vortex based on surface pressure feedback and synthetic jet described in the embodiments of this application, the frequency or phase difference of the synthetic jet is adjusted by inverting the optimal disturbance mechanism model until the flow field reaches a preset instability state, specifically including: Based on the optimal perturbation mode characteristics and the physical laws of tip vortex evolution obtained from the pre-solution analysis, an optimal perturbation mechanism model including synthetic jet parameters and flow field response mapping relationship is constructed. The threshold value of the instability characteristic parameter corresponding to the preset flow field instability state is used as the inversion target value. An improved gradient descent algorithm is used to minimize the error evaluation function. The iteration convergence condition is set as error, and the synthesized jet frequency and initial phase difference adjustment parameters that satisfy the convergence condition are obtained by inversion. The control command corresponding to the initial adjustment parameters is sent to the synthetic jet actuator, and real-time flow field pressure data is collected through the pressure sensor array to extract the actual flow field instability characteristic parameters. Calculate the deviation between the actual parameters and the target threshold. If the deviation exceeds the allowable range of ±10%, feed the actual parameters back to the optimal disturbance mechanism model, update the flow field boundary conditions of the model, and then re-execute the inversion solution until the flow field reaches the preset instability state.

[0010] Secondly, embodiments of this application provide an active wingtip vortex control system based on surface pressure feedback and synthetic jets. The system includes a memory and a processor. The memory includes a program for an active wingtip vortex control method based on surface pressure feedback and synthetic jets. When the program for the active wingtip vortex control method based on surface pressure feedback and synthetic jets is executed by the processor, it implements the following steps: Pressure data is collected in real time based on an array of pressure sensors arranged on the wing surface; time-frequency analysis is performed on the pressure data to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics. Based on the pre-solution analysis of the wingtip vortex optimal disturbance mode database, flow field characteristics are retrieved, and the dimensionless frequency, phase distribution, and spatial location information of the optimal external disturbance are matched to obtain dimensionless information. Dimensionless information is converted into driving frequency, driving voltage and phase commands for the synthetic jet actuator to control the actuator to generate a periodic jet that matches the optimal disturbance mode at a specific location; Continuously monitor the power spectral density and suction peak changes of pressure sensors at specific locations on the wing to determine whether the flow field meets the conditions for rapid instability; If the rapid instability condition is not met, the frequency or phase difference of the synthetic jet is adjusted by inverting the optimal disturbance mechanism model until the flow field reaches the preset instability state.

[0011] Optionally, in the active control system for wingtip vortex based on surface pressure feedback and synthetic jet described in the embodiments of this application, a high-bandwidth pressure sensor array is arranged on the upper and lower surfaces of the wingtip and near-wingtip region. The sensors are distributed along the chord and spanwise directions, and the spacing between adjacent sensors is set to 6~12mm; Real-time acquisition of unsteady pressure coefficients on the wing surface; comparison of time-averaged pressure values ​​at various points in the array based on the wingtip suction peak positioning principle. The key location is obtained by identifying the sensor position with the lowest average pressure, which corresponds to the projection of the wingtip vortex core onto the wing surface. Real-time Fast Fourier Transform (FFT) and bandpass filtering were performed on the pressure time-series signals from the key location and surrounding sensors to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics.

[0012] Optionally, in the active control system for wingtip vortex based on surface pressure feedback and synthetic jet described in the embodiments of this application, based on the wingtip vortex optimal disturbance mode database of pre-solution analysis, flow field characteristics are retrieved, and the dimensionless frequency, phase distribution, and spatial location information of the optimal external disturbance are matched to obtain dimensionless information, specifically including: Based on high-precision numerical simulation or wind tunnel experiments, a pre-solution analysis database is established for the target airfoil under different Reynolds numbers and angles of attack, storing the flow field response characteristics and optimal disturbance parameters corresponding to each working condition; Based on the pressure data, the Reynolds number, angle of attack, and wingtip vortex shedding frequency under the current operating conditions are extracted to obtain the real-time flow field characteristics; The real-time flow field characteristics are input into a pre-built database, and interpolation retrieval is performed to locate the pre-solution operator under the corresponding working condition. Solve the singular value decomposition of the retrieved pre-formula operator to obtain the right singular vector corresponding to the maximum singular value, and obtain the dimensionless frequency, phase distribution and spatial location information of the optimal external perturbation.

[0013] Thirdly, embodiments of this application also provide a computer-readable storage medium, which includes a program for an active wingtip vortex control method based on surface pressure feedback and synthetic jet. When the program for the active wingtip vortex control method based on surface pressure feedback and synthetic jet is executed by a processor, it implements the steps of the active wingtip vortex control method based on surface pressure feedback and synthetic jet as described in any of the preceding claims.

[0014] As can be seen from the above, the active control method, system, and medium for wingtip vortex based on surface pressure feedback and synthetic jet provided in this application involves real-time acquisition of pressure data using an array of pressure sensors arranged on the wing surface; time-frequency analysis of the pressure data to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics; retrieval of flow field characteristics based on a pre-solution wingtip vortex optimal disturbance mode database; matching the dimensionless frequency, phase distribution, and spatial location information of the optimal external disturbance to obtain dimensionless information; and conversion of the dimensionless information into a synthetic jet. The actuator's drive frequency, drive voltage, and phase commands control the actuator to generate a periodic jet at a specific location that matches the optimal disturbance mode. The power spectral density and suction peak changes of the pressure sensor at a specific location on the wing are continuously monitored to determine whether the flow field meets the rapid instability conditions. If the rapid instability conditions are not met, the frequency or phase difference of the synthesized jet is adjusted by inverting the optimal disturbance mechanism model until the flow field reaches the preset instability state. This invention can achieve rapid capture and closed-loop control from flow field data to the application of the optimal disturbance, effectively promoting the instability and rapid decay of wingtip vortices. Attached Figure Description

[0015] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments of this application will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0016] Figure 1 A flowchart of an active wingtip vortex control method based on surface pressure feedback and synthetic jet provided in an embodiment of this application; Figure 2 A flowchart of the active control method for wingtip vortex based on surface pressure feedback and synthetic jet in the preferred real-time mode of this application; Figure 3 A block diagram of an active control system for wingtip vortex based on surface pressure feedback and synthetic jet provided in this application embodiment; Figure 4 A schematic diagram of the pressure sensor distribution for an active control system for wingtip vortex based on surface pressure feedback and synthetic jet provided in an embodiment of this application; Figure 5 A schematic diagram of the connection of the disturbance simulation device for the active control system of wingtip vortex based on surface pressure feedback and synthetic jet provided in the embodiments of this application. Detailed Implementation

[0017] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of the embodiments. The components of the embodiments of this application described and shown in the accompanying drawings can generally be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of this application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but merely represents selected embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application.

[0018] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, in the description of this application, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0019] Please refer to Figures 1-2 As shown, the active wingtip vortex control method based on surface pressure feedback and synthetic jet is used in terminal equipment. This active wingtip vortex control method includes the following steps: S101, based on an array of pressure sensors arranged on the wing surface, collects pressure data in real time; performs time-frequency analysis on the pressure data to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics; S102, based on the pre-solution analysis of the wingtip vortex optimization disturbance mode database, retrieves flow field characteristics, matches the dimensionless frequency, phase distribution and spatial location information of the optimal external disturbance, and obtains dimensionless information; S103 converts dimensionless information into driving frequency, driving voltage and phase commands for the synthetic jet actuator to control the actuator to generate a periodic jet that matches the optimal disturbance mode at a specific position; S104 continuously monitors the power spectral density and suction peak changes of pressure sensors at specific locations on the wing to determine whether the flow field meets the conditions for rapid instability. S105 If the rapid instability condition is not met, the frequency or phase difference of the synthetic jet is adjusted by inverting the optimal disturbance mechanism model until the flow field reaches the preset instability state.

[0020] It should be noted that flow field characteristic perception and optimal mode matching are performed as follows: An array of pressure sensors deployed on the wing surface is used to collect unsteady pressure data in real time; time-frequency analysis (such as FFT) is performed on the pressure data to extract the current wingtip vortex shedding frequency and pressure fluctuation characteristics; combined with a pre-established wingtip vortex optimal disturbance mode database based on Resolvent Analysis, the dimensionless frequency, phase distribution, and spatial location information of the optimal external disturbance are retrieved and determined according to the current flow field characteristics. Physical domain parameter transformation and perturbation application: The above dimensionless information is transformed into the driving frequency, driving voltage (momentum coefficient) and phase command required by the synthetic jet actuator in the physical domain, and the synthetic jet actuator is controlled to generate a periodic jet that matches the optimal perturbation mode at a specific position, thereby exciting the instability of the wingtip vortex. Closed-loop feedback correction based on pressure spectrum characteristics: continuously monitor the power spectral density (PSD) and suction peak value changes of pressure sensors at specific locations on the wing (such as the trailing edge of the wingtip); determine whether the pressure signal exhibits the broadband characteristics and energy decay trend unique to vortex breaking; if the preset instability conditions are not met, use the optimal disturbance mechanism model to invert and adjust the frequency fine-tuning or phase difference of the synthetic jet until the flow field meets the rapid instability conditions.

[0021] According to an embodiment of the present invention, a high-bandwidth pressure sensor array is arranged on the upper and lower surfaces of the wingtip and near-wingtip regions; The sensors are distributed along the chord and spanwise directions, and the spacing between adjacent sensors is set to 6~12mm; Real-time acquisition of unsteady pressure coefficients on the wing surface; comparison of time-averaged pressure values ​​at various points in the array based on the wingtip suction peak positioning principle. The key location is obtained by identifying the sensor position with the lowest average pressure, which corresponds to the projection of the wingtip vortex core onto the wing surface. Real-time Fast Fourier Transform (FFT) and bandpass filtering were performed on the pressure time-series signals from the key location and surrounding sensors to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics.

[0022] According to an embodiment of the present invention, based on a pre-solution analysis-based wingtip vortex optimization perturbation mode database, flow field characteristics are retrieved, and the dimensionless frequency, phase distribution, and spatial location information of the optimal external perturbation are matched to obtain dimensionless information, specifically including: Based on high-precision numerical simulation or wind tunnel experiments, a pre-solution analysis database is established for the target airfoil under different Reynolds numbers and angles of attack, storing the flow field response characteristics and optimal disturbance parameters corresponding to each working condition; Based on the pressure data, the Reynolds number, angle of attack, and wingtip vortex shedding frequency under the current operating conditions are extracted to obtain the real-time flow field characteristics; The real-time flow field characteristics are input into a pre-built database, and interpolation retrieval is performed to locate the pre-solution operator under the corresponding working condition. Solve the singular value decomposition of the retrieved pre-formula operator to obtain the right singular vector corresponding to the maximum singular value, and obtain the dimensionless frequency, phase distribution and spatial location information of the optimal external perturbation.

[0023] According to an embodiment of the present invention, the driving frequency of the synthetic jet The calculation formula is as follows: in, For the incoming flow velocity, The average aerodynamic chord length; This represents the dimensionless Strauhal number.

[0024] The signal generator receives the above and The command, amplified by a power amplifier, drives a piezoelectric synthetic jet actuator embedded inside the wing. The actuator periodically injects and releases fluid at specific locations on the wingtip surface, injecting energy into the flow field that is highly matched with the "optimal disturbance mode," thereby inducing instability in the critical layer of the vortex core at the source.

[0025] It should be noted that, according to the optimal perturbation mode The spatial distribution of the modal amplitude is used to select the synthetic jet actuator located at the position of maximum amplitude for operation (e.g., if the modal sensitivity area is at the wingtip leading edge, then the leading edge actuator is activated). The actuator's output momentum coefficient... Set a fixed threshold, and the driving voltage Positive correlation.

[0026] According to embodiments of the present invention, the pre-solution operator The transfer function relationship between the external forced input and the flow response output in the linearized Navier-Stokes (NS) equations is described by the following formula: in, It is a state vector (velocity, pressure fluctuation). This is due to the external disturbance (i.e., the effect of the synthetic jet). To linearize the Navier-Stokes operator, singular value decomposition (SVD) is performed on the predicate operator, as shown in the following formula: in, Represents the maximum singular value and the corresponding right singular vector. This is the optimal perturbation mode.

[0027] Specifically, the criterion is to find the perturbation form that maximizes the flow field energy gain, that is, to excite the maximum flow field instability with the minimum input energy.

[0028] Online matching and calculation are performed based on the database: the control system reads the real-time flow field features (Reynolds number) extracted in step one. Angle of attack vortex shedding frequency The optimal dimensionless frequency in the current state is determined by interpolation retrieval in a pre-set database. And the optimal perturbation waveform and phase: i.e., the corresponding singular vector Spatial distribution characteristics.

[0029] According to an embodiment of the present invention, the frequency or phase difference of the synthetic jet is adjusted by inversion using an optimized disturbance mechanism model until the flow field reaches a preset instability state, specifically including: Based on the optimal perturbation mode characteristics and the physical laws of tip vortex evolution obtained from the pre-solution analysis, an optimal perturbation mechanism model including synthetic jet parameters and flow field response mapping relationship is constructed. The threshold value of the instability characteristic parameter corresponding to the preset flow field instability state is used as the inversion target value. An improved gradient descent algorithm is used to minimize the error evaluation function. The iterative convergence condition is set to an error less than a preset threshold, and the synthesized jet frequency and initial phase difference adjustment parameters that satisfy the convergence condition are obtained by inversion. The control command corresponding to the initial adjustment parameters is sent to the synthetic jet actuator, and real-time flow field pressure data is collected through the pressure sensor array to extract the actual flow field instability characteristic parameters. Calculate the deviation between the actual parameters and the target threshold. If the deviation exceeds the allowable range of ±10%, feed the actual parameters back to the optimal disturbance mechanism model, update the flow field boundary conditions of the model, and then re-execute the inversion solution until the flow field reaches the preset instability state.

[0030] It should be noted that pressure sensors are used to evaluate the control effect and perform closed-loop correction. The power spectral density (PSD) of pressure sensors at the wingtip trailing edge or specific locations is continuously monitored. If the wingtip vortex experiences rapid instability and breakup, the energy of the pressure signal will shift from concentrated at the dominant frequency. Broadband dissipation and time-averaged suction The absolute value of the peak value will decrease significantly (indicating a weakening of the vortex core intensity), at which point it can be determined as effective control. If the pressure spectrum peak value remains sharp and there is no frequency shift or amplitude attenuation, then it is ineffective control.

[0031] If the control is deemed "ineffective," the system will perform inversion based on the gradient-based optimization model to fine-tune the phase of the synthetic jet or slightly alter the driving frequency. (For example in) (Sweep frequency within range) until the broadband energy ratio fed back by the pressure sensor reaches the set threshold, then lock the current control parameters and complete the closed loop.

[0032] In summary, the present invention has the following beneficial effects: High engineering practicality and robustness: The pressure sensor is attached to the surface of the wing for measurement, which does not damage the aerodynamic shape. The structure is robust and more suitable for long-term monitoring and control in actual flight environments.

[0033] Precise and efficient perturbation application: Resolvent analysis is introduced as the criterion. Starting from the physical mechanism of energy gain amplification, the most sensitive perturbation mode (frequency and phase) of the flow field is accurately calculated, ensuring that the synthetic jet can excite the maximum vortex core instability effect with the minimum energy input.

[0034] Closed-loop intelligent control: A complete closed-loop link has been established from "pressure feature extraction" to "synthetic jet execution" and then to "pressure spectrum feedback". It can automatically adjust control parameters according to real-time changes in flight status (such as angle of attack and wind speed changes) to always maintain the best control effect.

[0035] like Figures 3-5 As shown, in a second aspect, embodiments of this application provide an active wingtip vortex control system based on surface pressure feedback and synthetic jets. The system includes a memory and a processor. The memory includes a program for an active wingtip vortex control method based on surface pressure feedback and synthetic jets. When the program for the active wingtip vortex control method based on surface pressure feedback and synthetic jets is executed by the processor, it implements the following steps: Based on an array of pressure sensors deployed on the wing surface, pressure data is collected in real time; time-frequency analysis is performed on the pressure data to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics. Based on the pre-solution analysis of the wingtip vortex optimal disturbance mode database, flow field characteristics are retrieved, and the dimensionless frequency, phase distribution, and spatial location information of the optimal external disturbance are matched to obtain dimensionless information. Dimensionless information is converted into driving frequency, driving voltage and phase commands for the synthetic jet actuator to control the actuator to generate a periodic jet that matches the optimal disturbance mode at a specific location; Continuously monitor the power spectral density and suction peak changes of pressure sensors at specific locations on the wing to determine whether the flow field meets the conditions for rapid instability; If the rapid instability condition is not met, the frequency or phase difference of the synthetic jet is adjusted by inverting the optimal disturbance mechanism model until the flow field reaches the preset instability state.

[0036] It should be noted that the system includes a measuring device: a high-bandwidth pressure sensor array embedded and mounted on the wing surface for non-invasive measurement of the time-varying pressure distribution on the wing surface; Computational processing unit: Used to receive pressure sensor signals, perform eddy frequency extraction, pre-solution modal matching calculation, and closed-loop feedback control law solution; The optimal disturbance simulation device includes a signal generator, a power amplifier, and a synthetic jet actuator, which executes control commands issued by the computing processing unit to generate a high-frequency synthetic jet.

[0037] According to an embodiment of the present invention, a high-bandwidth pressure sensor array is arranged on the upper and lower surfaces of the wingtip and near-wingtip regions; The sensors are distributed along the chord and spanwise directions, and the spacing between adjacent sensors is set to 6~12mm; Real-time acquisition of unsteady pressure coefficients on the wing surface; comparison of time-averaged pressure values ​​at various points in the array based on the wingtip suction peak positioning principle. The key location is obtained by identifying the sensor position with the lowest average pressure, which corresponds to the projection of the wingtip vortex core onto the wing surface. Real-time Fast Fourier Transform (FFT) and bandpass filtering were performed on the pressure time-series signals from the key location and surrounding sensors to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics.

[0038] According to an embodiment of the present invention, based on a pre-solution analysis-based wingtip vortex optimization perturbation mode database, flow field characteristics are retrieved, and the dimensionless frequency, phase distribution, and spatial location information of the optimal external perturbation are matched to obtain dimensionless information, specifically including: Based on high-precision numerical simulation or wind tunnel experiments, a pre-solution analysis database is established for the target airfoil under different Reynolds numbers and angles of attack, storing the flow field response characteristics and optimal disturbance parameters corresponding to each working condition; Based on the pressure data, the Reynolds number, angle of attack, and wingtip vortex shedding frequency under the current operating conditions are extracted to obtain the real-time flow field characteristics; The real-time flow field characteristics are input into a pre-built database, and interpolation retrieval is performed to locate the pre-solution operator under the corresponding working condition. Solve the singular value decomposition of the retrieved pre-formula operator to obtain the right singular vector corresponding to the maximum singular value, and obtain the dimensionless frequency, phase distribution and spatial location information of the optimal external perturbation.

[0039] A third aspect of the present invention provides a computer-readable storage medium including a program for an active wingtip vortex control method based on surface pressure feedback and synthetic jets. When the program is executed by a processor, it implements the steps of the active wingtip vortex control method based on surface pressure feedback and synthetic jets as described above.

[0040] This invention discloses an active control method, system, and medium for wingtip vortexes based on surface pressure feedback and synthetic jets. It utilizes an array of pressure sensors deployed on the wing surface to collect pressure data in real time; performs time-frequency analysis on the pressure data to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics; retrieves flow field characteristics based on a pre-solution wingtip vortex optimal disturbance mode database, and matches the dimensionless frequency, phase distribution, and spatial location information of the optimal external disturbance to obtain dimensionless information; and converts this dimensionless information into a synthetic jet actuator. The actuator is controlled by driving frequency, driving voltage, and phase commands to generate a periodic jet at a specific location that matches the optimal disturbance mode. The power spectral density and suction peak changes of the pressure sensor at a specific location on the wing are continuously monitored to determine whether the flow field meets the rapid instability conditions. If the rapid instability conditions are not met, the frequency or phase difference of the synthesized jet is adjusted by inverting the optimal disturbance mechanism model until the flow field reaches the preset instability state. This invention can achieve rapid capture and closed-loop control from flow field data to the application of the optimal disturbance, effectively promoting the instability and rapid decay of wingtip vortices.

[0041] In the several embodiments provided in this application, it should be understood that the disclosed devices and methods can be implemented in other ways. The device embodiments described above are merely illustrative. For example, the division of units is only a logical functional division, and in actual implementation, there may be other division methods, such as: multiple units or components can be combined, or integrated into another system, or some features can be ignored or not executed. In addition, the coupling, direct coupling, or communication connection between the various components shown or discussed can be through some interfaces, and the indirect coupling or communication connection between devices or units can be electrical, mechanical, or other forms.

[0042] The units described above as separate components may or may not be physically separate. The components shown as units may or may not be physical units. They may be located in one place or distributed across multiple network units. Some or all of the units may be selected to achieve the purpose of this embodiment according to actual needs.

[0043] In addition, in the various embodiments of the present invention, each functional unit can be integrated into one processing unit, or each unit can be a separate unit, or two or more units can be integrated into one unit; the integrated unit can be implemented in hardware or in the form of hardware plus software functional units.

[0044] Those skilled in the art will understand that all or part of the steps of the above method embodiments can be implemented by hardware related to program instructions. The aforementioned program can be stored in a readable storage medium. When the program is executed, it performs the steps of the above method embodiments. The aforementioned storage medium includes various media capable of storing program code, such as mobile storage devices, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0045] Alternatively, if the integrated units of the present invention are implemented as software functional modules and sold or used as independent products, they can also be stored in a readable storage medium. Based on this understanding, the technical solutions of the embodiments of the present invention, or the parts that contribute to the prior art, can be embodied in the form of a software product. This software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as mobile storage devices, ROM, RAM, magnetic disks, or optical disks.

Claims

1. A method for active control of wingtip vortices based on surface pressure feedback and synthetic jet, characterized in that, include: Pressure data is collected in real time based on an array of pressure sensors arranged on the wing surface; Time-frequency analysis was performed on the pressure data to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics; Based on the pre-solution analysis-based wingtip vortex optimization perturbation mode database, flow field characteristics are retrieved, and the dimensionless frequency, phase distribution, and spatial location information of the optimal external perturbation are matched to obtain dimensionless information, specifically including: Based on high-precision numerical simulation or wind tunnel experiments, a pre-solution analysis database is established for the target airfoil under different Reynolds numbers and angles of attack, storing the flow field response characteristics and optimal disturbance parameters corresponding to each working condition; Based on the pressure data, the Reynolds number, angle of attack, and wingtip vortex shedding frequency under the current operating conditions are extracted to obtain the real-time flow field characteristics; The real-time flow field characteristics are input into a pre-built database, and interpolation retrieval is performed to locate the pre-solution operator under the corresponding working condition. Solve the singular value decomposition of the retrieved pre-formula operator to obtain the right singular vector corresponding to the maximum singular value, and obtain the dimensionless frequency, phase distribution and spatial location information of the optimal external perturbation; Dimensionless information is converted into driving frequency, driving voltage and phase commands for the synthetic jet actuator to control the actuator to generate a periodic jet that matches the optimal disturbance mode at a specific location; Continuously monitor the power spectral density and suction peak changes of pressure sensors at specific locations on the wing to determine whether the flow field meets the conditions for rapid instability; If the rapid instability condition is not met, the frequency or phase difference of the synthetic jet is adjusted by inverting the optimal disturbance mechanism model until the flow field reaches the preset instability state.

2. The active control method for wingtip vortex based on surface pressure feedback and synthetic jet as described in claim 1, characterized in that, A high-bandwidth pressure sensor array is arranged on the upper and lower surfaces of the wingtip and near-wingtip region; The sensors are distributed along the chord and spanwise directions, and the spacing between adjacent sensors is set to 6~12mm; Real-time acquisition of unsteady pressure coefficients on the wing surface; comparison of time-averaged pressure values ​​at various points in the array based on the wingtip suction peak positioning principle. The key location is obtained by identifying the sensor position with the lowest average pressure, which corresponds to the projection of the wingtip vortex core onto the wing surface. Real-time Fast Fourier Transform (FFT) and bandpass filtering were performed on the pressure time-series signals from the key location and surrounding sensors to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics.

3. The active control method for wingtip vortex based on surface pressure feedback and synthetic jet as described in claim 1, characterized in that, Drive frequency of synthetic jet The calculation formula is as follows: in, For the incoming flow velocity, The average aerodynamic chord length; This represents the dimensionless Strauhal number.

4. The active control method for wingtip vortex based on surface pressure feedback and synthetic jet as described in claim 3, characterized in that, Pre-solution operator The transfer function relationship between the external forced input and the flow response output in the linearized Navier-Stokes (NS) equations is described by the following formula: in, For state vectors, For external disturbance, Let I be the linearized Navier-Stokes operator, and let I be the identity matrix. To resolve the frequency, singular value decomposition (SVD) is performed on the predicate operator, as shown in the following formula: The corresponding right singular vector This is the optimal perturbation mode, where Represents the maximum singular value. The singular values ​​obtained from the decomposition, These are the left and right singular vectors obtained from the decomposition, and the maximum value among the singular values ​​is represented as... The corresponding right singular vector This is the optimal perturbation mode.

5. The active control method for wingtip vortex based on surface pressure feedback and synthetic jet as described in claim 4, characterized in that, The frequency or phase difference of the synthetic jet is adjusted by inverting the optimal perturbation mechanism model until the flow field reaches a preset instability state, specifically including: Based on the optimal perturbation mode characteristics and the physical laws of tip vortex evolution obtained from the pre-solution analysis, an optimal perturbation mechanism model including synthetic jet parameters and flow field response mapping relationship is constructed. The threshold value of the instability characteristic parameter corresponding to the preset flow field instability state is used as the inversion target value. An improved gradient descent algorithm is used to minimize the error evaluation function. The iteration convergence condition is set as error, and the synthesized jet frequency and initial phase difference adjustment parameters that satisfy the convergence condition are obtained by inversion. The control command corresponding to the initial adjustment parameters is sent to the synthetic jet actuator, and real-time flow field pressure data is collected through the pressure sensor array to extract the actual flow field instability characteristic parameters. Calculate the deviation between the actual parameters and the target threshold. If the deviation exceeds the allowable range of ±10%, feed the actual parameters back to the optimal disturbance mechanism model, update the flow field boundary conditions of the model, and then re-execute the inversion solution until the flow field reaches the preset instability state.

6. An active control system for wingtip vortex based on surface pressure feedback and synthetic jet, characterized in that, The system includes a memory and a processor. The memory contains a program for an active wingtip vortex control method based on surface pressure feedback and synthetic jets. When the program for the active wingtip vortex control method based on surface pressure feedback and synthetic jets is executed by the processor, it performs the following steps: Pressure data is collected in real time based on an array of pressure sensors arranged on the wing surface; time-frequency analysis is performed on the pressure data to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics. Based on the pre-solution analysis-based wingtip vortex optimization perturbation mode database, flow field characteristics are retrieved, and the dimensionless frequency, phase distribution, and spatial location information of the optimal external perturbation are matched to obtain dimensionless information, specifically including: Based on high-precision numerical simulation or wind tunnel experiments, a pre-solution analysis database is established for the target airfoil under different Reynolds numbers and angles of attack, storing the flow field response characteristics and optimal disturbance parameters corresponding to each working condition; Based on the pressure data, the Reynolds number, angle of attack, and wingtip vortex shedding frequency under the current operating conditions are extracted to obtain the real-time flow field characteristics; The real-time flow field characteristics are input into a pre-built database, and interpolation retrieval is performed to locate the pre-solution operator under the corresponding working condition. Solve the singular value decomposition of the retrieved pre-formula operator to obtain the right singular vector corresponding to the maximum singular value, and obtain the dimensionless frequency, phase distribution and spatial location information of the optimal external perturbation; Dimensionless information is converted into driving frequency, driving voltage and phase commands for the synthetic jet actuator to control the actuator to generate a periodic jet that matches the optimal disturbance mode at a specific location; Continuously monitor the power spectral density and suction peak changes of pressure sensors at specific locations on the wing to determine whether the flow field meets the conditions for rapid instability; If the rapid instability condition is not met, the frequency or phase difference of the synthetic jet is adjusted by inverting the optimal disturbance mechanism model until the flow field reaches the preset instability state.

7. The active control system for wingtip vortex based on surface pressure feedback and synthetic jet as described in claim 6, characterized in that, A high-bandwidth pressure sensor array is arranged on the upper and lower surfaces of the wingtip and near-wingtip region; The sensors are distributed along the chord and spanwise directions, and the spacing between adjacent sensors is set to 6~12mm; Real-time acquisition of unsteady pressure coefficients on the wing surface; comparison of time-averaged pressure values ​​at various points in the array based on the wingtip suction peak positioning principle. The key location is obtained by identifying the sensor position with the lowest average pressure, which corresponds to the projection of the wingtip vortex core onto the wing surface. Real-time Fast Fourier Transform (FFT) and bandpass filtering were performed on the pressure time-series signals from the key location and surrounding sensors to extract the current wingtip vortex shedding frequency and pressure pulsation characteristics.

8. A computer-readable storage medium, characterized in that, The computer-readable storage medium includes a program for an active wingtip vortex control method based on surface pressure feedback and synthetic jets. When the program is executed by a processor, it implements the steps of the active wingtip vortex control method based on surface pressure feedback and synthetic jets as described in any one of claims 1 to 5.

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