Stall flutter suppression methods, systems, equipment, and media for airfoil structures

Abstract

This application relates to the field of vibration control technology, specifically providing a method, system, device, and medium for suppressing stall flutter in airfoil structures, aiming to solve the problem of how to accurately tune and effectively suppress stall flutter. The airfoil structure of this application includes an airfoil component and a tuned mass damper. The method includes: constructing a continuous state-space model of the airfoil structure; acquiring aerodynamic information of the airfoil structure; determining adjustment parameters of the tuned mass damper based on the aerodynamic information and the continuous state-space model of the airfoil structure; and adjusting the tuned mass damper based on the adjustment parameters to suppress stall flutter in the airfoil structure. This application determines the parameters of the tuned mass damper based on the continuous state-space model of the airfoil structure, and then uses the tuned mass damper to suppress flutter in the airfoil structure, reduce structural damage, and extend its service life.

Description

Technical Field

[0001] This application relates to the field of vibration control technology, specifically to a method, system, device, and medium for suppressing stall flutter in an airfoil structure. Background Technology

[0002] When an airfoil operates at high angles of attack or in strong gusts, flow separation occurs at its trailing edge. This is characterized by the generation, convection, and shedding of stall separation vortices, resulting in significant nonlinear hysteresis in the aerodynamic forces, leading to a sudden increase in drag and fluctuations in the aerodynamic center position. Due to the interaction between the nonlinear aerodynamic forces generated by airflow separation during dynamic stall and the inertial forces and structure, unsteady aerodynamic forces and the flexible structure are coupled, causing aeroelastic self-excited vibrations in the structure—a phenomenon known as stall flutter.

[0003] Stall flutter can lead to structural fatigue and even damage. Because stall flutter involves large-scale flow separation and reattachment with high aerodynamic nonlinearity, this repeated loading and unloading process can cause fatigue in structural materials, potentially leading to structural damage or failure in the long term, resulting in significant safety hazards and economic losses. During wind turbine operation, the performance of the wind turbine airfoil (i.e., wind turbine blades) is affected by factors such as airflow and wind speed changes, making it prone to stall and flutter, severely impacting the power output and structural safety of the wind turbine. Stall causes the airfoil to lose lift and generate significant aerodynamic drag, while flutter, the self-excited vibration of the airfoil or other aerodynamic surfaces under specific aerodynamic loads, often leads to structural fatigue and even damage. Traditional flutter suppression methods include structural design optimization, the application of damping materials, and aerodynamic control systems; however, these methods often suffer from increased structural weight, high complexity, or high cost.

[0004] Accordingly, there is a need in the field for a new stall flutter suppression scheme to address the above problems. Summary of the Invention

[0005] In order to overcome the above-mentioned deficiencies, this application is made to solve, or at least partially solve, the technical problem of how to achieve precise tuning and effectively suppress stall flutter.

[0006] In a first aspect, a method for suppressing stall flutter in an airfoil structure is provided. The airfoil structure includes an airfoil component and a tuned mass damper. The method includes: constructing a continuous state-space model of the airfoil structure; acquiring aerodynamic information of the airfoil structure; determining adjustment parameters of the tuned mass damper based on the aerodynamic information and the continuous state-space model of the airfoil structure; and adjusting the tuned mass damper based on the adjustment parameters to suppress stall flutter in the airfoil structure.

[0007] In one technical solution of the above-mentioned airfoil structure stall flutter suppression method, the step of constructing a continuous state space model of the airfoil structure includes: obtaining parameter information of the airfoil and the tuned mass damper; and constructing a continuous state space model of the airfoil structure based on the parameter information of the airfoil and the tuned mass damper.

[0008] In one technical solution of the above-mentioned airfoil structure stall flutter suppression method, the step of constructing a continuous state space model of the airfoil structure based on the parameter information of the airfoil and the tuned mass damper includes: establishing the structural motion equation of the airfoil structure based on the parameter information of the airfoil and the tuned mass damper; and obtaining the continuous state space model of the airfoil structure based on the structural motion equation of the airfoil structure.

[0009] In one technical solution of the stall flutter suppression method for the aforementioned airfoil structure, the step of establishing the structural motion equation of the airfoil structure based on the parameter information of the airfoil structure and the tuned mass damper includes: establishing the structural motion equation of the airfoil component based on the parameter information of the airfoil component, wherein the parameter information of the airfoil component includes the mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, flutter angular acceleration, and aerodynamic information of the airfoil component; and establishing the structural motion equation of the airfoil structure based on the structural motion equation of the airfoil component and the parameter information of the tuned mass damper, wherein the parameter information of the tuned mass damper includes the mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, and flutter angular acceleration of the tuned mass damper.

[0010] In one technical solution of the above-mentioned airfoil structure stall flutter suppression method, obtaining the continuous state space model of the airfoil structure based on the structural motion equation of the airfoil structure includes: converting the structural motion equation of the airfoil structure into a differential form based on the flutter angular displacement of the airfoil and the tuned mass damper; defining state variables; and determining the continuous state space model of the airfoil structure based on the state variables and the differential form of the structural motion equation.

[0011] In one technical solution of the above-mentioned stall flutter suppression method for airfoil structures, the step of determining the adjustment parameters of the tuned mass damper based on the aerodynamic information and the continuous state space model of the airfoil structure includes: solving the continuous state space model of the airfoil structure based on the aerodynamic information, and determining the adjustment parameters of the tuned mass damper when the calculation results meet preset conditions.

[0012] In one technical solution of the stall flutter suppression method for the aforementioned airfoil structure, the aerodynamic information includes the torque generated by the aerodynamic force acting on the airfoil structure; the step of solving the continuous state space model of the airfoil structure based on the aerodynamic information, and determining the adjustment parameters of the tuned mass damper when the calculation result meets preset conditions, includes: substituting the torque generated by the aerodynamic force acting on the airfoil structure into the continuous state space model of the airfoil structure to calculate the flutter angular displacement of the airfoil; and determining the adjustment parameters of the tuned mass damper when the flutter angular displacement of the airfoil meets preset conditions, wherein the adjustment parameters include the mass, damping, and spring stiffness of the tuned mass damper.

[0013] In a second aspect, a stall flutter suppression system for an airfoil structure is provided. The airfoil structure includes an airfoil element and a tuned mass damper. The system includes: a construction module for constructing a continuous state-space model of the airfoil structure; an acquisition module for acquiring aerodynamic information of the airfoil structure; a determination module for determining adjustment parameters of the tuned mass damper based on the aerodynamic information and the continuous state-space model of the airfoil structure; and an adjustment module for adjusting the tuned mass damper based on the adjustment parameters to suppress stall flutter of the airfoil structure.

[0014] In a third aspect, an electronic device is provided, comprising at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores a computer program, which, when executed by the at least one processor, implements the method described in any one of the above-described methods for stall flutter suppression of airfoil structures.

[0015] In a fourth aspect, a computer-readable storage medium is provided, wherein a plurality of program codes are stored therein, the program codes being adapted to be loaded and run by a processor to perform the method described in any of the technical solutions of the above-described airfoil structure stall flutter suppression method.

[0016] The above-described technical solutions of this application have at least one or more of the following beneficial effects:

[0017] This application provides a stall flutter suppression method for airfoil structures, wherein the airfoil structure includes an airfoil component and a tuned mass damper. The method includes: constructing a continuous state-space model of the airfoil structure; acquiring aerodynamic information of the airfoil structure; determining adjustment parameters of the tuned mass damper based on the aerodynamic information and the continuous state-space model of the airfoil structure; and adjusting the tuned mass damper based on the adjustment parameters to suppress stall flutter of the airfoil structure. This application, by constructing a continuous state-space model of the airfoil structure, can determine the coupling relationship between the airfoil component and the tuned mass damper. Furthermore, based on the aerodynamic information and the continuous state-space model of the airfoil structure, it can determine the adjustment parameters of the tuned mass damper when stall flutter occurs in the airfoil structure. Adjusting the tuned mass damper according to these parameters can effectively suppress stall flutter of the airfoil structure, prevent structural damage due to stall flutter, extend its service life, and ensure the safe operation of the airfoil structure. Attached Figure Description

[0018] The disclosure of this application will become more readily understood with reference to the accompanying drawings. It will be readily understood by those skilled in the art that these drawings are for illustrative purposes only and are not intended to limit the scope of protection of this application. Wherein:

[0019] Figure 1 This is a schematic flowchart of the main steps of a stall flutter suppression method for an airfoil structure according to an embodiment of this application;

[0020] Figure 2 This is a schematic diagram of the kinematic model of stall flutter of an airfoil structure according to an embodiment of this application;

[0021] Figure 3 This is a simplified model schematic diagram of a tuned mass damper according to an embodiment of this application;

[0022] Figure 4 This is a schematic diagram of the main structure of a stall flutter suppression system for an airfoil structure according to an embodiment of this application;

[0023] Figure 5 This is a schematic diagram of the main structure of an electronic device according to an embodiment of this application.

[0024] Figure label:

[0025] 11: Memory; 12: Processor; 41: Building module; 42: Acquisition module; 43: Determination module; 44: Adjustment module. Detailed Implementation

[0026] Some embodiments of this application are described below with reference to the accompanying drawings. Those skilled in the art should understand that these embodiments are merely illustrative of the technical principles of this application and are not intended to limit the scope of protection of this application.

[0027] In the description of this application, "module" and "processor" can include hardware, software, or a combination of both. A module can include hardware circuitry, various suitable sensors, communication ports, memory, and may also include software components, such as program code, or a combination of software and hardware. A processor can be a central processing unit, microprocessor, image processor, digital signal processor, or any other suitable processor. The processor has data and / or signal processing capabilities. The processor can be implemented in software, in hardware, or a combination of both. Computer-readable storage media includes any suitable medium capable of storing program code, such as magnetic disks, hard disks, optical disks, flash memory, read-only memory, random access memory, etc. The term "A and / or B" means all possible combinations of A and B, such as only A, only B, or A and B. The terms "at least one A or B" or "at least one of A and B" have a similar meaning to "A and / or B" and can include only A, only B, or A and B. The singular terms "a" or "this" can also include plural forms.

[0028] Here we will first explain some of the terms used in this application.

[0029] Tuned mass dampers (TMDs) are a classic vibration control device widely used in structures such as buildings and bridges. They effectively absorb and suppress vibrations by adding a component with specific mass, stiffness, and damping to the system. In the aerospace field, tuned mass dampers are also increasingly being studied for mitigating airfoil flutter.

[0030] Under specific operating conditions of airfoil structures (such as high angle-of-attack flight and strong gusts), flow separation occurs at the airfoil's trailing edge, leading to the generation, convection, and shedding of stall separation vortices. This results in significant nonlinear hysteresis characteristics in the aerodynamic forces, causing a sudden increase in drag and fluctuations in the aerodynamic center position. Due to the interaction between the nonlinear aerodynamic forces generated by airflow separation during dynamic stall and the inertial forces and structure, unsteady aerodynamic forces and the flexible structure are coupled, causing aeroelastic self-excited vibrations—a phenomenon known as stall flutter. Stall flutter can lead to structural fatigue and even failure. In wind turbine operation, stall flutter in the airfoil severely affects its power output and structural safety. Currently, traditional flutter suppression methods include structural design optimization, the application of damping materials, and aerodynamic control systems. However, these methods often suffer from increased structural weight, high complexity, or high cost. Therefore, how to suppress stall flutter while ensuring the operational performance and stability of the airfoil is a pressing issue that needs to be addressed.

[0031] Therefore, this application provides a stall flutter suppression method for airfoil structures, wherein the airfoil structure includes an airfoil component and a tuned mass damper. The method includes: constructing a continuous state-space model of the airfoil structure; acquiring aerodynamic information of the airfoil structure; determining adjustment parameters of the tuned mass damper based on the aerodynamic information and the continuous state-space model of the airfoil structure; and adjusting the tuned mass damper based on the adjustment parameters to suppress stall flutter of the airfoil structure. This application, by constructing a continuous state-space model of the airfoil structure, can determine the coupling relationship between the airfoil component and the tuned mass damper. Furthermore, based on the aerodynamic information and the continuous state-space model of the airfoil structure, it can determine the adjustment parameters of the tuned mass damper when stall flutter occurs in the airfoil structure. Adjusting the tuned mass damper according to these parameters can effectively suppress stall flutter of the airfoil structure, prevent structural damage due to stall flutter, extend its service life, and ensure the safe operation of the airfoil structure.

[0032] See appendix Figure 1 , Figure 1 This is a schematic flowchart illustrating the main steps of a stall flutter suppression method for an airfoil structure according to an embodiment of this application. Figure 1 As shown in the embodiment of this application, the stall flutter suppression method of the airfoil structure includes an airfoil component and a tuned mass damper, and mainly includes the following steps S101 to S104.

[0033] Step S101: Construct a continuous state-space model of the airfoil structure.

[0034] In this embodiment, the airfoil can be an aircraft wing or a wind turbine blade. Since the vertical cross-section of an aircraft wing and a wind turbine blade is a two-dimensional airfoil, it is simplified to a two-dimensional airfoil structure.

[0035] Step S102: Obtain the aerodynamic information of the airfoil structure.

[0036] Step S103: Based on the aerodynamic information and the continuous state-space model of the airfoil structure, determine the adjustment parameters of the tuned mass damper.

[0037] Step S104: Adjust the tuned mass damper based on the adjustment parameters to suppress the stall flutter phenomenon of the airfoil structure.

[0038] Based on the methods described in steps S101 to S104 above, this application can determine the coupling relationship between the airfoil and the tuned mass damper by constructing a continuous state space model of the airfoil structure. Then, based on the aerodynamic information and the continuous state space model of the airfoil structure, the adjustment parameters of the tuned mass damper when the airfoil structure experiences stall flutter can be obtained. By adjusting the tuned mass damper according to these adjustment parameters, the stall flutter of the airfoil structure can be effectively suppressed, and the structural damage caused by the stall flutter of the airfoil structure can be prevented, thereby extending its service life and ensuring the safe operation of the airfoil structure.

[0039] The following provides further explanation of steps S101 to S104.

[0040] For step S101: Construct a continuous state-space model of the airfoil structure.

[0041] In one embodiment, constructing the continuous state-space model of the airfoil structure includes: obtaining parameter information of the airfoil and the tuned mass damper; and constructing the continuous state-space model of the airfoil structure based on the parameter information of the airfoil and the tuned mass damper.

[0042] Specifically, it is assumed that the vertical cross-section of an aircraft wing and a wind turbine blade is a two-dimensional airfoil. A two-dimensional airfoil has only one rotational degree of freedom and can rotate freely around the center of rotation. Its structural motion system is a mass-damping-spring system.

[0043] Kinematic model of airfoil stall flutter as follows Figure 2 As shown, the airfoil structure undergoes a single-degree-of-freedom pitch motion around its rotation center. The relationship between the incoming flow angle of attack, the flutter angular displacement of the airfoil structure, and the torsional angle of the airfoil structure installation can be expressed as:

[0044] α=θ0+θ1 (1)

[0045] Where θ0 is the torsion angle of the airfoil installation, θ1 is the flutter angular displacement of the airfoil, and α is the angle of attack of the incoming flow.

[0046] Based on this assumption, the parameter information of the airfoil and the tuned mass damper is obtained, and a continuous state-space model of the airfoil structure is constructed based on the parameter information of the airfoil and the tuned mass damper.

[0047] In one embodiment, constructing a continuous state-space model of the airfoil structure based on the parameter information of the airfoil and the tuned mass damper includes: establishing the structural motion equations of the airfoil structure based on the parameter information of the airfoil and the tuned mass damper; and obtaining the continuous state-space model of the airfoil structure based on the structural motion equations of the airfoil structure.

[0048] In one embodiment, establishing the structural motion equation of the airfoil structure based on the parameter information of the airfoil structure and the tuned mass damper includes: establishing the structural motion equation of the airfoil component based on the parameter information of the airfoil component, wherein the parameter information of the airfoil component includes the mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, flutter angular acceleration, and aerodynamic information of the airfoil component; and establishing the structural motion equation of the airfoil structure based on the structural motion equation of the airfoil component and the parameter information of the tuned mass damper, wherein the parameter information of the tuned mass damper includes the mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, and flutter angular acceleration of the tuned mass damper.

[0049] Specifically, based on the airfoil's mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, flutter angular acceleration, and aerodynamic information, the structural motion equations of the airfoil are established. Here, the aerodynamic information refers to the torque exerted by aerodynamic forces on the airfoil. The structural motion equations of the airfoil are expressed as follows:

[0050]

[0051] Where θ1 is the flutter angular displacement of the airfoil. The flutter angular velocity of the airfoil. Let m1 be the flutter angular acceleration of the airfoil, c1 be the mass of the airfoil, k1 be the damping of the airfoil, k1 be the spring stiffness of the airfoil, and F1 be the torque of the aerodynamic force on the airfoil.

[0052] The tuned mass damper consists of a uniform mass block, a spring, and a damper. Its mounting center coincides with the airfoil's rotation center. A simplified model of the tuned mass damper is shown below. Figure 3 As shown.

[0053] Based on the established structural motion equations of the airfoil and the parameter information of the tuned mass damper, the structural motion equations of the airfoil structure with the tuned mass damper installed are determined, which are expressed as:

[0054]

[0055] Where c2 is the damping of the tuned mass damper, k2 is the spring stiffness of the tuned mass damper, and θ2 is the flutter angular displacement of the tuned mass damper. To tune the flutter angular acceleration of the mass damper, denoted as flutter angular velocity of the tuned mass damper, m2 as the mass of the tuned mass damper, and F as the torque generated by the aerodynamic force acting on the airfoil structure.

[0056] In one embodiment, obtaining a continuous state-space model of the airfoil structure based on its structural motion equations includes: converting the structural motion equations of the airfoil structure into differential form based on the flutter angular displacements of the airfoil and the tuned mass damper; defining state variables; and determining the continuous state-space model of the airfoil structure based on the state variables and the differential form of the structural motion equations.

[0057] Specifically, based on the flutter angular displacement of the airfoil and the tuned mass damper, let the displacement matrix ξ be:

[0058]

[0059] Using the displacement matrix ξ, the structural motion equations of the airfoil structure are transformed into differential form structural motion equations, which are expressed as follows:

[0060]

[0061] Where M is the mass matrix, G is the damping matrix, K is the stiffness matrix, F is the torque matrix, and ξ is the flutter angular displacement matrix. The first derivative of the flutter angular displacement matrix. The second derivative of the flutter angular displacement matrix, where,

[0062]

[0063] Define the state variables as follows:

[0064]

[0065] in, It is the first derivative of the displacement matrix.

[0066] By introducing state variables, the differential form of the structural motion equations is transformed into a continuous state-space model of the airfoil structure, as shown in the following expression:

[0067]

[0068] Where F(t) is the torque matrix, and t is time. C s =[E 0], D s = [0], where E is the identity matrix.

[0069] For step S102, the aerodynamic information of the airfoil structure is obtained.

[0070] Specifically, the aerodynamic information of an airfoil structure refers to the torque generated by aerodynamic forces acting on the airfoil structure.

[0071] For step S103, based on the aerodynamic information and the continuous state-space model of the airfoil structure, the adjustment parameters of the tuned mass damper are determined.

[0072] In one embodiment, determining the adjustment parameters of the tuned mass damper based on the aerodynamic information and the continuous state-space model of the airfoil structure includes: solving the continuous state-space model of the airfoil structure based on the aerodynamic information, and determining the adjustment parameters of the tuned mass damper when the calculation results meet preset conditions.

[0073] In one embodiment, the aerodynamic information includes the torque generated by the aerodynamic forces acting on the airfoil structure; the step of solving the continuous state-space model of the airfoil structure based on the aerodynamic information, and determining the adjustment parameters of the tuned mass damper when the calculation results meet preset conditions, includes: substituting the torque generated by the aerodynamic forces acting on the airfoil structure into the continuous state-space model of the airfoil structure to determine the flutter angular displacement of the airfoil; and determining the adjustment parameters of the tuned mass damper when the flutter angular displacement of the airfoil meets preset conditions, wherein the adjustment parameters include the mass parameter, damping parameter, and spring stiffness parameter of the tuned mass damper.

[0074] Specifically, the torque generated by the aerodynamic force acting on the airfoil structure is substituted into formulas (3) to (5), and the three parameters of the tuned mass damper, the mass, damping and spring stiffness are changed. By adjusting these parameters, the influence of the tuned mass damper on the flutter angular displacement of the airfoil structure under different configurations can be determined.

[0075] For each tuned mass damper parameter configuration, calculate the flutter angular displacement of the airfoil and the flutter angular displacement of the tuned mass damper, and determine whether the flutter angular displacement of the airfoil is the minimum flutter angular displacement. If the flutter angular displacement of the airfoil reaches the minimum flutter angular displacement, it is determined that the preset condition is met, and the mass parameter, damping parameter, and spring stiffness parameter of the tuned mass damper corresponding to this flutter angular displacement are used as adjustment parameters.

[0076] If the flutter angular displacement of the current configuration is not the minimum, continue to change the mass, damping, and spring stiffness of the tuned mass damper, and repeat the above calculation process until the tuned mass damper parameter configuration that minimizes the flutter angular displacement of the airfoil structure is found.

[0077] In step S104, the tuned mass damper is adjusted based on the adjustment parameters to suppress the stall flutter phenomenon of the airfoil structure.

[0078] Specifically, based on the calculated adjustment parameters, the mass, damping, and spring stiffness of the tuned mass damper are adjusted to make the natural frequency of the tuned mass damper close to the natural frequency of the airfoil. When the airfoil is subjected to external excitation and vibrates, the tuned mass damper generates an inertial force opposite to the vibration direction, converting the vibration of the airfoil into its own vibration and dissipating it, thereby attenuating the vibration of the airfoil, reducing the vibration amplitude of the airfoil and suppressing its vibration response, thus improving the stability and safety of the airfoil structure.

[0079] In some specific embodiments, the method of this application can be applied to the design of helicopter rotors and turbine blades to effectively control stall flutter of airfoil structures under extreme conditions such as high angle of attack flight or encountering strong gusts, thereby improving flight safety and performance.

[0080] In some specific embodiments, by applying the method of this application, it is possible to suppress blade flutter of wind turbine blades when they are operating at high wind speeds by adjusting the tuned mass damper, thereby reducing blade damage and extending their service life.

[0081] In some specific embodiments, the method of this application can also be used to analyze and control aeroelastic dynamic response, which is of great significance for vibration energy harvesting and preventing structural damage.

[0082] It should be noted that although the steps in the above embodiments are described in a specific order, those skilled in the art will understand that in order to achieve the effect of this application, different steps do not necessarily have to be executed in such an order. They can be executed simultaneously (in parallel) or in other orders. These adjusted solutions are equivalent to the technical solutions described in this application and therefore will also fall within the protection scope of this application.

[0083] Those skilled in the art will understand that all or part of the processes in the method of the above-described embodiment can also be implemented by a computer program instructing related hardware. The computer program can be stored in a computer-readable storage medium, and when executed by a processor, it can implement the steps of the various method embodiments described above. The computer program includes computer program code, which can be in the form of source code, object code, executable file, or some intermediate form. The computer-readable storage medium can include any entity or device capable of carrying the computer program code, a medium, a USB flash drive, a portable hard drive, a magnetic disk, an optical disk, a computer memory, a read-only memory, a random access memory, an electrical carrier signal, a telecommunication signal, and a software distribution medium, etc.

[0084] Another aspect of this application provides a stall flutter suppression system for an airfoil structure.

[0085] See appendix Figure 4 , Figure 4 This is a schematic diagram of the main structure of a stall flutter suppression system for an airfoil structure according to an embodiment of this application. Figure 4 As shown, the stall flutter suppression system for the airfoil structure in this embodiment mainly includes a construction module 41, an acquisition module 42, a determination module 43, and an adjustment module 44. In some embodiments, one or more of the construction module 41, acquisition module 42, determination module 43, and adjustment module 44 can be combined into a single module. In some embodiments, the construction module 41 can be configured to construct a continuous state-space model of the airfoil structure. The acquisition module 42 can be configured to acquire aerodynamic information of the airfoil structure. The determination module 43 can be configured to determine the adjustment parameters of the tuned mass damper based on the aerodynamic information and the continuous state-space model of the airfoil structure. The adjustment module 44 can be configured to adjust the tuned mass damper based on the adjustment parameters to suppress the stall flutter phenomenon of the airfoil structure. In one embodiment, a description of the specific functions can be found in steps S101 to S104.

[0086] The aforementioned airfoil structure's stall flutter suppression system is used for execution Figure 1 The embodiments of the stall flutter suppression method for airfoil structures shown are similar in technical principle, the technical problems solved, and the technical effects produced. Those skilled in the art can clearly understand that, for the sake of convenience and brevity, the specific working process and related descriptions of the stall flutter suppression system for airfoil structures can be found in the embodiments of the stall flutter suppression method for airfoil structures, and will not be repeated here.

[0087] Another aspect of this application provides an electronic device.

[0088] See appendix Figure 5 , Figure 5 The illustration exemplarily shows a memory 11 and a processor 12 connected in communication via a bus. In an embodiment of an electronic device according to this application, the electronic device may include at least one processor; and a memory communicatively connected to the at least one processor; wherein the memory stores a computer program that, when executed by the at least one processor, implements the methods described in any of the above embodiments. The electronic device described in this application may include driving equipment, intelligent vehicles, robots, and other devices.

[0089] Another aspect of this application provides a computer-readable storage medium.

[0090] In one embodiment of a computer-readable storage medium according to this application, the computer-readable storage medium may be configured to store a program for performing the stall flutter suppression method for an airfoil structure according to the above-described method embodiments. This program may be loaded and run by a processor to implement the stall flutter suppression method for the airfoil structure. For ease of explanation, only the parts related to the embodiments of this application are shown; for specific technical details not disclosed, please refer to the method section of the embodiments of this application. The computer-readable storage medium may be a storage device comprising various electronic devices. Optionally, in the embodiments of this application, the computer-readable storage medium is a non-transitory computer-readable storage medium.

[0091] The technical solution of this application has been described above with reference to one embodiment shown in the accompanying drawings. However, it will be readily understood by those skilled in the art that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for suppressing stall flutter in an airfoil structure, characterized in that, The airfoil structure includes an airfoil element and a tuned mass damper, and the method includes: A continuous state space model of the airfoil structure is constructed, wherein the continuous state space model is obtained by defining state variables after coupling the structural motion equation of the airfoil with the parameter information of the tuned mass damper. The continuous state space model represents the coupling relationship between the airfoil and the tuned mass damper. Obtain the aerodynamic information of the airfoil structure; Based on the aerodynamic information and the continuous state-space model of the airfoil structure, the adjustment parameters of the tuned mass damper are determined. The adjustment parameters include the mass parameter, damping parameter, and spring stiffness parameter of the tuned mass damper. The tuned mass damper is adjusted based on the aforementioned adjustment parameters to suppress stall flutter in the airfoil structure.

2. The stall flutter suppression method for airfoil structures according to claim 1, characterized in that, The construction of the continuous state-space model of the airfoil structure includes: Obtain the parameter information of the airfoil and the tuned mass damper; Based on the parameter information of the airfoil and the tuned mass damper, a continuous state-space model of the airfoil structure is constructed.

3. The stall flutter suppression method for airfoil structures according to claim 2, characterized in that, The construction of a continuous state-space model of the airfoil structure based on the parameter information of the airfoil and the tuned mass damper includes: Based on the parameter information of the airfoil and the tuned mass damper, the structural motion equation of the airfoil structure is established. Based on the structural motion equations of the airfoil structure, a continuous state-space model of the airfoil structure is obtained.

4. The stall flutter suppression method for airfoil structures according to claim 3, characterized in that, The process of establishing the structural motion equations of the airfoil structure based on the parameter information of the airfoil structure and the tuned mass damper includes: Based on the parameter information of the airfoil, the structural motion equation of the airfoil is established, wherein the parameter information of the airfoil includes the mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, flutter angular acceleration and aerodynamic information of the airfoil; Based on the structural motion equation of the airfoil and the parameter information of the tuned mass damper, the structural motion equation of the airfoil structure is established. The parameter information of the tuned mass damper includes the mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, and flutter angular acceleration of the tuned mass damper.

5. The stall flutter suppression method for airfoil structures according to claim 4, characterized in that, The continuous state-space model of the airfoil structure is obtained based on the structural motion equations of the airfoil structure, including: Based on the flutter angular displacement of the airfoil and the tuned mass damper, the structural motion equation of the airfoil structure is converted into a differential form of the structural motion equation; Define state variables, and based on the state variables and the differential form of the structural motion equations, determine the continuous state-space model of the airfoil structure.

6. The stall flutter suppression method for an airfoil structure according to claim 1, characterized in that, The determination of the adjustment parameters of the tuned mass damper based on the aerodynamic information and the continuous state-space model of the airfoil structure includes: Based on the aerodynamic information, a continuous state-space model of the airfoil structure is solved, and the adjustment parameters of the tuned mass damper are determined if the calculation results meet preset conditions.

7. The stall flutter suppression method for airfoil structures according to claim 6, characterized in that, The aerodynamic information includes the torque generated by aerodynamic forces acting on the airfoil structure; the process of solving the continuous state-space model of the airfoil structure based on the aerodynamic information, and determining the adjustment parameters of the tuned mass damper when the calculation results meet preset conditions, includes: The torque generated by the aerodynamic force acting on the airfoil structure is substituted into the continuous state space model of the airfoil structure to determine the flutter angular displacement of the airfoil component. When the flutter angular displacement of the airfoil meets the preset conditions, the adjustment parameters of the tuned mass damper are determined.

8. A stall flutter suppression system for an airfoil structure, characterized in that, The airfoil structure includes an airfoil element and a tuned mass damper, and the system includes: A construction module is used to construct a continuous state space model of the airfoil structure. The continuous state space model is obtained by defining state variables after coupling the structural motion equations of the airfoil with the parameter information of the tuned mass damper. The continuous state space model represents the coupling relationship between the airfoil and the tuned mass damper. The acquisition module is used to acquire the aerodynamic information of the airfoil structure; The determination module is used to determine the adjustment parameters of the tuned mass damper based on the aerodynamic information and the continuous state space model of the airfoil structure. The adjustment parameters include the mass parameter, damping parameter and spring stiffness parameter of the tuned mass damper. An adjustment module is used to adjust the tuned mass damper based on the adjustment parameters to suppress stall flutter of the airfoil structure.

9. An electronic device comprising at least one processor and at least one memory, said memory being adapted to store a plurality of program codes, characterized in that, The program code is adapted to be loaded and run by the processor to perform the stall flutter suppression method for the airfoil structure according to any one of claims 1 to 7.

10. A computer-readable storage medium storing a plurality of program codes, characterized in that, The program code is adapted to be loaded and run by a processor to perform the stall flutter suppression method for the airfoil structure according to any one of claims 1 to 7.

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