Stall flutter suppression method, system and equipment of airfoil structure and medium

Abstract

The invention relates to the technical field of vibration control, particularly provides a stall flutter suppression method, system and equipment of an airfoil structure and a medium, and aims to solve the problem of how to accurately tune and effectively suppress stall flutter. The airfoil structure comprises an airfoil part and a tuned mass damper. The method comprises the following steps: constructing a continuous state space model of the airfoil structure; aerodynamic force information of the airfoil structure is obtained; based on the aerodynamic force information and a continuous state space model of the airfoil structure, adjusting parameters of the tuned mass damper are determined; and the tuned mass damper is adjusted on the basis of the adjusting parameters so as to restrain the stall flutter phenomenon of the airfoil structure. Based on the continuous state space model of the airfoil structure, the parameters of the tuned mass damper are determined, flutter of the airfoil structure is restrained through the tuned mass damper, structural damage is reduced, and the service life of the airfoil structure is prolonged.

Description

Technical Field

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

[0002] When the airfoil is in high angle of attack flight, strong gusts and other operating conditions, flow separation will occur at its trailing edge, with the characteristic features of the generation, convection and shedding of the stall separation vortex, and the aerodynamic force will show obvious nonlinear hysteresis characteristics, with a sudden increase in resistance and fluctuations in the aerodynamic center position. Due to the interaction between the nonlinear aerodynamic force generated by the separation of the airflow during dynamic stall and the inertial force and structure, the unsteady aerodynamic force and the flexible structure are coupled with each other, and the structure will experience aeroelastic self-excited vibration, which is called stall flutter.

[0003] Stall flutter may cause fatigue or even damage to the structure. Since stall flutter involves large-scale flow separation and reattachment, the aerodynamic force is highly nonlinear. This repeated loading and unloading process will cause fatigue of the structural materials, which may cause damage or failure of the structure in the long run, resulting in huge safety hazards and economic losses. During the operation of the wind turbine, the performance of the wind turbine airfoil (i.e., wind turbine blades) is affected by factors such as airflow changes and wind speed changes, and stall and flutter phenomena are prone to occur, which seriously affect the power output and structural safety of the wind turbine. Stall will cause the airfoil to lose lift and generate large aerodynamic drag. Flutter is the self-excited vibration of the wing or other aerodynamic surfaces under specific aerodynamic loads, which often causes structural fatigue or even damage. Traditional flutter suppression methods include structural design optimization, damping material application, and aerodynamic control systems. However, these methods often have problems such as increased structural weight, high complexity, or high cost.

[0004] Accordingly, a new stall flutter suppression solution is needed in the art to solve the above problems. Summary of the invention

[0005] In order to overcome the above-mentioned defects, the present application is proposed 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 of an airfoil structure is provided, wherein the airfoil structure includes an airfoil member and a tuned mass damper, and 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 the stall flutter phenomenon of the airfoil structure.

[0007] In a technical solution of the stall flutter suppression method of the above-mentioned airfoil structure, constructing a continuous state space model of the airfoil structure includes: acquiring 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 a technical solution of the stall flutter suppression method of the above-mentioned airfoil structure, the continuous state space model of the airfoil structure is constructed based on the parameter information of the airfoil and the tuned mass damper, including: 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 a technical solution of the stall flutter suppression method of the above-mentioned airfoil structure, the structural motion equation of the airfoil structure is established based on the parameter information of the airfoil structure and the tuned mass damper, including: establishing the structural motion equation of the airfoil based on the parameter information of the airfoil, wherein the parameter information of the airfoil includes the mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, flutter angular acceleration and aerodynamic force information of the airfoil; establishing the structural motion equation of the airfoil structure based on the structural motion equation of the airfoil 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 a technical solution of the stall flutter suppression method of the above-mentioned airfoil structure, the continuous state space model of the airfoil structure is obtained based on the structural motion equation of the airfoil structure, including: converting the structural motion equation of the airfoil structure into a structural motion equation in 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 structural motion equation in differential form.

[0011] In a technical solution of the stall flutter suppression method of the above-mentioned airfoil structure, determining the adjustment parameters of the tuned mass damper based on the aerodynamic force 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 force information, and determining the adjustment parameters of the tuned mass damper when the calculation results meet preset conditions.

[0012] In a technical solution of the stall flutter suppression method of the above-mentioned airfoil structure, the aerodynamic force information includes the torque generated by the aerodynamic force acting on the airfoil structure; the continuous state space model of the airfoil structure is solved based on the aerodynamic force information, and when the calculation result meets the preset conditions, the adjustment parameters of the tuned mass damper are determined, including: substituting the torque generated by the aerodynamic force acting on the airfoil structure into the continuous state space model of the airfoil structure, and calculating the flutter angular displacement of the airfoil; when the flutter angular displacement of the airfoil meets the preset conditions, determining the adjustment parameters of the tuned mass damper, the adjustment parameters including the mass, damping and spring stiffness of the tuned mass damper.

[0013] In a second aspect, a stall flutter suppression system of an airfoil structure is provided, wherein the airfoil structure includes an airfoil member and a tuned mass damper, and 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 the stall flutter phenomenon 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 a computer program is stored in the memory, and when the computer program is executed by the at least one processor, the method described in any one of the technical solutions of the method for suppressing stall flutter of the above-mentioned airfoil structure is implemented.

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

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

[0017] The present application provides a method for suppressing stall flutter of an airfoil structure, wherein the airfoil structure includes an airfoil and a tuned mass damper, and the method includes: constructing a continuous state space model of the airfoil structure; obtaining 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 the stall flutter phenomenon of the airfoil structure. The present 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, and then according to the aerodynamic information and the continuous state space model of the airfoil structure, it can know the adjustment parameters of the tuned mass damper when the airfoil structure has a stall flutter phenomenon, and adjust the tuned mass damper according to the adjustment parameters, which can effectively suppress the stall flutter of the airfoil structure, and prevent the airfoil structure from being structurally damaged due to stall flutter, thereby extending the service life and ensuring the safe operation of the airfoil structure. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The disclosure of the present application will become easier to understand with reference to the accompanying drawings. It is easy for those skilled in the art to understand that these drawings are only for illustrative purposes and are not intended to limit the scope of protection of the present application. Among them:

[0019] Figure 1 is a schematic flow chart of main steps of a method for suppressing stall flutter of an airfoil structure according to an embodiment of the present application;

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

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

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

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

[0024] Reference numerals:

[0025] 11: memory; 12: processor; 41: construction module; 42: acquisition module; 43: determination module; 44: adjustment module. DETAILED DESCRIPTION

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

[0027] In the description of the present application, "module" and "processor" may include hardware, software or a combination of the two. A module may include hardware circuits, various suitable sensors, communication ports, memory, and may also include software parts, such as program code, or a combination of software and hardware. The processor may be a central processing unit, a microprocessor, an image processor, a digital signal processor or any other suitable processor. The processor has data and / or signal processing functions. The processor may be implemented in software, hardware or a combination of the two. Computer-readable storage media include any suitable medium that can store program code, such as a disk, a hard disk, an optical disk, a flash memory, a read-only memory, a 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 term "at least one A or B" or "at least one of A and B" has a similar meaning to "A and / or B" and may include only A, only B or A and B. The singular terms "one" and "the" may also include plural forms.

[0028] Here we first explain some terms involved in this application.

[0029] Tuned mass damper (TMD) is a classic vibration control device, widely used in buildings, bridges and other structures, which effectively absorbs and suppresses vibration by adding a component with specific mass, stiffness and damping to the system. In the field of aviation, tuned mass dampers are also gradually being studied for mitigating the flutter of airfoils.

[0030] Under specific operating conditions of the airfoil structure (such as high angle of attack flight, strong gusts, etc.), flow separation will occur at the trailing edge of the airfoil, leading to the generation, convection and shedding of the stall separation vortex, and the aerodynamic force will show obvious nonlinear hysteresis characteristics, with a sudden increase in resistance and fluctuations in the aerodynamic center position. Due to the interaction between the nonlinear aerodynamic force generated by the airflow separation during dynamic stall and the inertial force and structure, the unsteady aerodynamic force and the flexible structure are coupled with each other, and the structure exhibits aeroelastic self-excited vibration, which is called stall flutter. Stall flutter may cause structural fatigue or even damage. During the operation of the wind turbine, the stall flutter of the wind turbine airfoil will seriously affect its power output and structural safety. At present, traditional flutter suppression methods include structural design optimization, damping material application, and aerodynamic control systems, but these methods often have problems such as increased structural weight, high complexity or high cost. Therefore, how to suppress stall flutter while ensuring the operating performance and stability of the airfoil is an urgent problem to be solved.

[0031] To this end, the present application provides a method for suppressing stall flutter of an airfoil structure, wherein the airfoil structure includes an airfoil and a tuned mass damper, and the method includes: constructing a continuous state space model of the airfoil structure; obtaining 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 the stall flutter phenomenon of the airfoil structure. The present 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, and then according to the aerodynamic information and the continuous state space model of the airfoil structure, it can know the adjustment parameters of the tuned mass damper when the airfoil structure has a stall flutter phenomenon, and adjust the tuned mass damper according to the adjustment parameters, which can effectively suppress the stall flutter of the airfoil structure, and prevent the airfoil structure from being structurally damaged due to stall flutter, thereby extending the service life and ensuring the safe operation of the airfoil structure.

[0032] See attached Figure 1 , Figure 1 FIG. 1 is a flow chart of the main steps of a method for suppressing stall flutter of an airfoil structure according to an embodiment of the present application. Figure 1 As shown, the stall flutter suppression method of the airfoil structure in the embodiment of the present application, wherein the airfoil structure includes an airfoil member and a tuned mass damper, mainly includes the following steps S101 to S104.

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

[0034] In this embodiment, the airfoil may be an aircraft wing or a wind turbine blade. Since the vertical sections of the aircraft wing and the wind turbine blade are two-dimensional airfoils, they are simplified into two-dimensional airfoil structures.

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

[0036] Step S103: determining adjustment parameters of the tuned mass damper based on the aerodynamic force information and the continuous state space model of the airfoil structure.

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

[0038] Based on the methods described in steps S101 to S104 above, the present 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, and then according to the aerodynamic information and the continuous state-space model of the airfoil structure, it can obtain the adjustment parameters of the tuned mass damper when the airfoil structure suffers from stall flutter, and adjust the tuned mass damper according to the adjustment parameters, which can effectively suppress the stall flutter of the airfoil structure, prevent the airfoil structure from being damaged due to stall flutter, extend the service life, and ensure the safe operation of the airfoil structure.

[0039] The above steps S101 to S104 are further explained below.

[0040] With respect to step S101: constructing a continuous state space model of the airfoil structure.

[0041] In one embodiment, constructing the continuous state space model of the airfoil structure includes: acquiring 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 the aircraft wing and the wind turbine blade is a two-dimensional airfoil. The 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-damper-spring system.

[0043] The kinematic model of stall flutter of airfoil structure is as follows: Figure 2 As shown, the airfoil structure performs a single-degree-of-freedom pitch motion around the rotation center. The relationship between the incoming flow angle of attack and the flutter angular displacement of the airfoil structure and the torsion angle of the airfoil structure installation can be expressed as: α=θ 0 +θ 1 (1)

[0044] Among them, θ 0 is the twist angle of the airfoil structure installation, θ 1 is the flutter angular displacement of the airfoil structure, and α is the incoming flow attack angle.

[0045] 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 according to the parameter information of the airfoil and the tuned mass damper.

[0046] In one embodiment, constructing a continuous state-space model of the airfoil structure based on parameter information of the airfoil and the tuned mass damper includes: establishing a structural motion equation of the airfoil structure based on parameter information of the airfoil and the tuned mass damper; and obtaining a continuous state-space model of the airfoil structure based on the structural motion equation of the airfoil structure.

[0047] In one embodiment, the establishing of 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 based on the parameter information of the airfoil, wherein the parameter information of the airfoil includes the mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, flutter angular acceleration and aerodynamic force information of the airfoil; establishing the structural motion equation of the airfoil structure based on the structural motion equation of the airfoil 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.

[0048] Specifically, based on the mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, flutter angular acceleration and aerodynamic information of the airfoil, the structural motion equation of the airfoil is established, wherein the aerodynamic information refers to the torque of the aerodynamic force on the airfoil. The structural motion equation of the airfoil is expressed as:

[0049] Among them, θ 1 is the flutter angular displacement of the airfoil, is the flutter angular velocity of the airfoil, is the flutter angular acceleration of the airfoil, m 1 is the mass of the airfoil, c 1 is the damping of the airfoil, k 1 is the spring stiffness of the airfoil, F 1 is the torque of the aerodynamic force on the airfoil.

[0050] The tuned mass damper consists of a uniform mass block, a spring and a damper. The installation center is consistent with the airfoil rotation center. The simplified model of the tuned mass damper is as follows: Figure 3 shown.

[0051] Based on the established structural motion equation of the airfoil and the parameter information of the tuned mass damper, the structural motion equation of the tuned mass damper is determined, that is, the structural motion equation of the airfoil structure, which is expressed as:

[0052] Among them, c 2is the damping of the tuned mass damper, k 2 is the spring stiffness of the tuned mass damper, θ 2 is the flutter angular displacement of the tuned mass damper, is the flutter angular acceleration of the tuned mass damper, is the flutter angular velocity of the tuned mass damper, m 2 is the mass of the tuned mass damper, and F is the torque generated by the aerodynamic force acting on the airfoil structure.

[0053] In one embodiment, 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 structural motion equation in 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 structural motion equation in differential form.

[0054] Specifically, based on the flutter angular displacement of the airfoil and the tuned mass damper, the displacement matrix ξ is assumed to be:

[0055] Using the displacement matrix ξ, the structural motion equation of the airfoil structure is converted into the structural motion equation in differential form. The structural motion equation in differential form is expressed as:

[0056] Among them, M is the mass matrix, G is the damping matrix, K is the stiffness matrix, F is the torque matrix, ξ is the flutter angular displacement matrix, is the first-order derivative of the flutter angular displacement matrix, The second derivative of the flutter angular displacement matrix, where

[0057]

[0058] Define the state variables as:

[0059] in, is the first-order derivative of the displacement matrix.

[0060] By introducing state variables, the structural motion equation in differential form is converted into a continuous state space model of the airfoil structure in continuous state space form. The expression is as follows:

[0061] Where F(t) is the torque matrix, t is time, C s=[E 0],D s =[0], where E is the unit matrix.

[0062] With respect to step S102, aerodynamic information of the airfoil structure is obtained.

[0063] Specifically, the aerodynamic information of the airfoil structure refers to the torque generated by the aerodynamic force acting on the airfoil structure.

[0064] With respect to step S103, adjustment parameters of the tuned mass damper are determined based on the aerodynamic force information and the continuous state space model of the airfoil structure.

[0065] In one embodiment, determining the adjustment parameters of the tuned mass damper based on the aerodynamic force 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 force information, and determining the adjustment parameters of the tuned mass damper when the calculation results meet preset conditions.

[0066] In one embodiment, the aerodynamic force information includes the torque generated by the aerodynamic force acting on the airfoil structure; the continuous state-space model of the airfoil structure is solved based on the aerodynamic force information, and when the calculation result meets the preset conditions, the adjustment parameters of the tuned mass damper are determined, including: substituting the torque generated by the aerodynamic force acting on the airfoil structure into the continuous state-space model of the airfoil structure to determine the flutter angular displacement of the airfoil; when the flutter angular displacement of the airfoil meets the preset conditions, determining the adjustment parameters of the tuned mass damper, the adjustment parameters including the mass parameters, damping parameters and spring stiffness parameters of the tuned mass damper.

[0067] 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, namely 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.

[0068] For each tuned mass damper parameter configuration, the flutter angular displacement of the airfoil and the flutter angular displacement of the tuned mass damper are calculated, and it is determined 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 and it is determined that the preset conditions are met, the mass parameter, damping parameter and spring stiffness parameter of the tuned mass damper corresponding to the flutter angular displacement are used as adjustment parameters.

[0069] If the flutter angular displacement of the current configuration is not the minimum, the mass, damping and spring stiffness of the tuned mass damper continue to be changed, and the above calculation process is repeated until the tuned mass damper parameter configuration that minimizes the flutter angular displacement of the airfoil structure is found.

[0070] With respect to step S104, the tuned mass damper is adjusted based on the adjustment parameter to suppress stall flutter phenomenon of the airfoil structure.

[0071] Specifically, based on the calculated adjustment parameters, the mass, damping and spring stiffness of the tuned mass damper are adjusted respectively, so that the natural frequency of the tuned mass damper is close to the natural frequency of the airfoil. When the airfoil is vibrated by external excitation, the tuned mass damper generates an inertial force in the opposite direction of the vibration, which converts the vibration of the airfoil into its own vibration and consumes it, so that the vibration of the airfoil is attenuated, the vibration amplitude of the airfoil is reduced and its vibration response is suppressed, thereby improving the stability and safety of the airfoil structure.

[0072] In some specific embodiments, the method of the present application is applied in the design of helicopter rotors and turbine blades to effectively control the stall flutter of the airfoil structure under extreme conditions such as flying at high angles of attack or encountering strong gusts, thereby improving flight safety and performance.

[0073] In some specific embodiments, by applying the method of the present application, the blade flutter occurring when the blades of a wind turbine operate at high wind speeds can be suppressed by adjusting the tuned mass damper, thereby reducing damage to the blades and extending their service life.

[0074] In some specific embodiments, the method of the present application can also be used to analyze and control aeroelastic dynamic response, which is of great significance for vibration energy capture and prevention of structural damage.

[0075] It should be pointed out that although the various steps in the above embodiments are described in a specific order, those skilled in the art can understand that in order to achieve the effect of the present application, different steps do not have to be executed in such an order. They can be executed simultaneously (in parallel) or in other orders. These adjusted schemes are equivalent to the technical schemes described in this application, and therefore will also fall within the scope of protection of this application.

[0076] It is understood by those skilled in the art that all or part of the processes in the method for implementing the above-mentioned embodiment of the present application can also be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a computer-readable storage medium, and the computer program can implement the steps of the above-mentioned various method embodiments when executed by the processor. Among them, the computer program includes computer program code, and the computer program code can be in source code form, object code form, executable file or some intermediate form. The computer-readable storage medium may include: any entity or device, medium, U disk, mobile hard disk, disk, optical disk, computer memory, read-only memory, random access memory, electrical carrier signal, telecommunication signal and software distribution medium, etc. that can carry the computer program code.

[0077] Another aspect of the present application provides a stall flutter suppression system for an airfoil structure.

[0078] See attached Figure 4 , Figure 4 FIG. 1 is a schematic diagram of the main structure of a stall flutter suppression system for an airfoil structure according to an embodiment of the present application. Figure 4 As shown, the stall flutter suppression system of the airfoil structure in the embodiment of the present application 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, the acquisition module 42, the determination module 43, and the adjustment module 44 can be combined into one 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 obtain 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, the description of the specific implementation function can be referred to steps S101 to S104.

[0079] The stall flutter suppression system of the above airfoil structure is used to perform Figure 1 The stall flutter suppression method embodiment of the airfoil structure shown in the figure has similar technical principles, technical problems solved and technical effects produced. Those skilled in the art can clearly understand that for the convenience and brevity of description, the specific working process and related instructions of the stall flutter suppression system of the airfoil structure can refer to the contents described in the embodiment of the stall flutter suppression method of the airfoil structure, which will not be repeated here.

[0080] Another aspect of the present application provides an electronic device.

[0081] See attached Figure 5 , Figure 5 In the example, it is shown that the memory 11 and the processor 12 are connected by bus communication. In an embodiment of an electronic device according to the present application, the electronic device may include at least one processor; and a memory connected to the at least one processor; wherein a computer program is stored in the memory, and when the computer program is executed by at least one processor, the method described in any of the above embodiments is implemented. The electronic device described in the present application may include driving equipment, smart cars, robots and other equipment.

[0082] Another aspect of the present application also provides a computer-readable storage medium.

[0083] In an embodiment of a computer-readable storage medium according to the present application, the computer-readable storage medium may be configured to store a program for executing the stall flutter suppression method of the airfoil structure of the above method embodiment, and the program may be loaded and run by a processor to implement the stall flutter suppression method of the above airfoil structure. For ease of explanation, only the parts related to the embodiment of the present application are shown. For specific technical details not disclosed, please refer to the method part of the embodiment of the present application. The computer-readable storage medium may be a storage device formed by various electronic devices. Optionally, the computer-readable storage medium in the embodiment of the present application is a non-transitory computer-readable storage medium.

[0084] So far, the technical solution of the present application has been described in conjunction with an embodiment shown in the accompanying drawings, but it is easy for those skilled in the art to understand that the protection scope of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present 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 fall within the protection scope of the present application.

Claims

1. A method for suppressing stall flutter of an airfoil structure, characterized in that: The airfoil structure comprises an airfoil and a tuned mass damper, and the method comprises: 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 force information and a continuous state space model of the airfoil structure; The tuned mass damper is adjusted based on the adjustment parameter to suppress stall flutter phenomenon of the airfoil structure.

2. The stall flutter suppression method of an airfoil structure according to claim 1, characterized in that: The continuous state space model of the airfoil structure is constructed, comprising: Acquiring parameter information of the airfoil and the tuned mass damper; A continuous state space model of the airfoil structure is constructed based on parameter information of the airfoil and the tuned mass damper.

3. The stall flutter suppression method of an airfoil structure according to claim 2, characterized in that: The step of constructing a continuous state space model of the airfoil structure based on parameter information of the airfoil and the tuned mass damper comprises: Establishing a structural motion equation of the airfoil structure based on parameter information of the airfoil and the tuned mass damper; Based on the structural motion equation of the airfoil structure, a continuous state space model of the airfoil structure is obtained.

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

5. The stall flutter suppression method of an airfoil structure according to claim 4, characterized in that: The continuous state space model of the airfoil structure is obtained based on the structural motion equation of the airfoil structure, including: converting a structural equation of motion of the airfoil structure into a structural equation of motion in differential form based on the flutter angular displacement of the airfoil and the tuned mass damper; State variables are defined, and a continuous state space model of the airfoil structure is determined based on the state variables and the structural motion equations in differential form.

6. The stall flutter suppression method of an airfoil structure according to claim 1, characterized in that: The step of determining adjustment parameters of the tuned mass damper based on the aerodynamic force information and the continuous state space model of the airfoil structure comprises: A continuous state space model of the airfoil structure is solved based on the aerodynamic force information, and when a calculation result meets a preset condition, an adjustment parameter of the tuned mass damper is determined.

7. The stall flutter suppression method of an airfoil structure according to claim 6, characterized in that: The aerodynamic force information includes the torque generated by the aerodynamic force acting on the airfoil structure; solving the continuous state space model of the airfoil structure based on the aerodynamic force information, and determining the adjustment parameters of the tuned mass damper when the calculation result meets the preset conditions, includes: Substituting the torque generated by the aerodynamic force acting on the airfoil structure into a continuous state space model of the airfoil structure to determine the flutter angular displacement of the airfoil; When the flutter angular displacement of the airfoil meets a preset condition, adjustment parameters of the tuned mass damper are determined, wherein the adjustment parameters include a mass parameter, a damping parameter, and a spring stiffness parameter of the tuned mass damper.

8. A stall flutter suppression system for an airfoil structure, characterized in that: The airfoil structure includes an airfoil and a tuned mass damper, and the system includes: A construction module, used for constructing a continuous state space model of the airfoil structure; An acquisition module, used to acquire aerodynamic information of the airfoil structure; A determination module, configured to determine adjustment parameters of the tuned mass damper based on the aerodynamic force information and a continuous state space model of the airfoil structure; The regulating module is used to regulate the tuned mass damper based on the regulating parameter to suppress the stall flutter phenomenon of the airfoil structure.

9. An electronic device comprising at least one processor and at least one memory, wherein the memory is suitable for storing a plurality of program codes, wherein: The program code is suitable for being loaded and run by the processor to execute the stall flutter suppression method of 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 suitable for being loaded and run by a processor to execute the stall flutter suppression method of the airfoil structure according to any one of claims 1 to 7.

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