Method, system and equipment for evaluating stall flutter stability of airfoil structure and medium

Abstract

The invention relates to the technical field of vibration evaluation, and particularly provides an airfoil structure stall flutter stability evaluation method, system and device and a medium. The airfoil structure comprises an airfoil part and a tuned mass damper, and the airfoil structure stall flutter stability evaluation method comprises the steps that a continuous state space equation of the airfoil structure is constructed based on structure parameters of the airfoil structure; based on system identification, constructing a continuous state space equation of the aerodynamic system; based on the continuous state space equation of the airfoil structure and the continuous state space equation of the aerodynamic system, constructing a state space analysis model of a coupling system; and evaluating the stall flutter stability of the airfoil structure based on the state space analysis model of the coupling system. According to the method, aeroelastic stability analysis and optimization design can be carried out on the airfoil structure with the tuned mass damper, so that the safety of the airfoil structure in the operation process is effectively guaranteed, and personal and property losses are reduced.

Description

Technical Field

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

[0002] In the fields of aviation and wind energy, stall flutter is a typical aeroelastic instability phenomenon, which usually occurs when the structure is flying at a high angle of attack or encountering strong gusts of wind. This type of phenomenon involves complex aeroelastic interactions and nonlinear aerodynamic characteristics, and is common in key components such as large wind turbine blades, helicopter rotors, and aircraft wings. Under the action of stall separation flow, these elastic structures are prone to large frequency-locked vibrations. This vibration will not only significantly reduce the aerodynamic efficiency of the structure, but also reduce the critical flutter speed, leading to structural fatigue or even damage, posing a serious threat to flight performance and safety. Therefore, evaluating and analyzing the stall flutter behavior of airfoil structures is crucial to ensuring the safe operation of aviation and wind energy equipment.

[0003] Accordingly, the art needs a new airfoil structure stall flutter stability assessment scheme to solve the above problems. Summary of the invention

[0004] In order to overcome the above-mentioned defects, the present application is proposed to solve or at least partially solve the technical problem of evaluating the stall flutter stability of an airfoil structure.

[0005] In a first aspect, a method for evaluating the stall flutter stability 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 equation of the airfoil structure based on structural parameters of the airfoil structure; constructing a continuous state-space equation of an aerodynamic system based on system identification; constructing a state-space analysis model of a coupled system based on the continuous state-space equation of the airfoil structure and the continuous state-space equation of the aerodynamic system; and evaluating the stall flutter stability of the airfoil structure based on the state-space analysis model of the coupled system.

[0006] In a technical solution of the above-mentioned method for evaluating the stall flutter stability of an airfoil structure, the continuous state space equation of the airfoil structure is constructed based on the structural parameters of the airfoil structure, including: establishing the structural motion equation of the airfoil structure based on the structural parameters of the airfoil structure; and constructing the continuous state space equation of the airfoil structure based on the structural motion equation of the airfoil structure.

[0007] In a technical solution of the above-mentioned method for evaluating the stall flutter stability of an airfoil structure, the structural parameters of the airfoil structure include parameter information of an airfoil member and parameter information of a tuned mass damper; the establishing of a structural motion equation of the airfoil structure based on the structural parameters of the airfoil structure includes: establishing a structural motion equation of the airfoil structure based on the parameter information of the airfoil member and the parameter information of the tuned mass damper, wherein the parameter information of the airfoil member includes mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, flutter angular acceleration and aerodynamic force information, and the parameter information of the tuned mass damper includes mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity and flutter angular acceleration. In a technical solution of the above-mentioned method for evaluating the stall flutter stability of the airfoil structure, the continuous state space equation of the airfoil structure is constructed 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; defining state variables, and converting the structural motion equation in differential form into a continuous state space equation using the state variables.

[0008] In a technical solution of the above-mentioned method for evaluating the stall flutter stability of an airfoil structure, the continuous state space equation of the aerodynamic system is constructed based on system identification, including: establishing a multi-input and multi-output autoregressive model based on system identification, the input data of the autoregressive model being the flutter angular displacement of the airfoil structure, and the output data being the torque of the aerodynamic force on the airfoil structure; defining a state vector, and using the state vector to convert the autoregressive model into a discrete state space equation; performing a bilinear transformation on the discrete state space equation to obtain a continuous state space equation of the aerodynamic system.

[0009] In a technical solution of the above-mentioned method for evaluating the stall flutter stability of an airfoil structure, a state space analysis model of a coupled system is constructed based on the continuous state space equations of the airfoil structure and the continuous state space equations of the aerodynamic system, including: coupling the continuous state space equations of the airfoil structure and the continuous state space equations of the aerodynamic system to form a closed-loop feedback process, and obtaining the state space analysis model of the coupled system.

[0010] In a technical solution of the above-mentioned method for evaluating the stall flutter stability of the airfoil structure, the stall flutter stability of the airfoil structure is evaluated based on the state-space analysis model of the coupling system, including: solving the matrix eigenvalues ​​of the state-space analysis model of the coupling system, the real part of the matrix eigenvalues ​​is the damping of the coupling system, and the imaginary part is the frequency of the coupling system; based on the matrix eigenvalues, the stall flutter stability of the airfoil structure is evaluated to determine the stable state of the airfoil structure.

[0011] In a second aspect, a stall flutter stability assessment system for an airfoil structure is provided, wherein the airfoil structure comprises an airfoil member and a tuned mass damper, and the system comprises: a first building module, for constructing a continuous state-space equation of the airfoil structure based on structural parameters of the airfoil structure; a second building module, for constructing a continuous state-space equation of an aerodynamic system based on system identification; a third building module, for constructing a state-space analysis model of a coupled system based on the continuous state-space equation of the airfoil structure and the continuous state-space equation of the aerodynamic system; and an assessment module, for assessing the stall flutter stability of the airfoil structure based on the state-space analysis model of the coupled system.

[0012] 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 above-mentioned method for evaluating stall flutter stability of an airfoil structure is implemented.

[0013] 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 evaluating stall flutter stability of an airfoil structure.

[0014] The above one or more technical solutions of the present application have at least one or more of the following beneficial effects:

[0015] The present application provides a method for evaluating the stall flutter stability of an airfoil structure, wherein the airfoil structure includes an airfoil member and a tuned mass damper, and the method includes: constructing a continuous state space equation of the airfoil structure based on structural parameters of the airfoil structure; constructing a continuous state space equation of the aerodynamic system based on system identification; constructing a state space analysis model of a coupled system based on the continuous state space equation of the airfoil structure and the continuous state space equation of the aerodynamic system; and evaluating the stall flutter stability of the airfoil structure based on the state space analysis model of the coupled system. The present application constructs a state space analysis model of a coupled system by coupling the continuous state space equation of the airfoil structure and the continuous state space equation of the aerodynamic system, comprehensively considering the structural and aerodynamic characteristics, and can more truly reflect the actual working conditions, significantly improve the accuracy of stall flutter stability evaluation, and provide accurate data support for the optimal design of the airfoil structure, thereby effectively ensuring the safety of the airfoil structure during operation and reducing personal and property losses. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] 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:

[0017] Figure 1 is a schematic flow chart of the main steps of a method for evaluating stall flutter stability of an airfoil structure according to an embodiment of the present application;

[0018] Figure 2 is a schematic diagram of a kinematic model of an airfoil structure according to an embodiment of the present application;

[0019] Figure 3 is a schematic flow chart of main steps of a system for evaluating stall flutter stability of an airfoil structure according to another embodiment of the present application;

[0020] Figure 4 is a main structural schematic diagram of an airfoil structure stall flutter stability assessment system according to an embodiment of the present application;

[0021] Figure 5 It is a schematic diagram of the main structure of an electronic device according to an embodiment of the present application.

[0022] Reference numerals:

[0023] 11: memory; 12: processor; 41: first building block; 42: second building block; 43: third building block; 44: evaluation module. DETAILED DESCRIPTION

[0024] 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.

[0025] 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.

[0026] In the fields of aviation and wind energy, stall flutter usually occurs when the structure is flying at a high angle of attack or encountering strong gusts of wind. Stall flutter involves complex aeroelastic interactions and nonlinear aerodynamic characteristics, and is common in key components such as large wind turbine blades, helicopter rotors, and aircraft wings. Under the action of stall separation flow, the elastic structure of these structures is very prone to large frequency-locked vibrations. This vibration will not only significantly reduce the aerodynamic efficiency of the structure, but also reduce the critical flutter speed, leading to structural fatigue or even damage, posing a serious threat to flight performance and safety.

[0027] To this end, the present application provides a method for evaluating the stall flutter stability of an airfoil structure, wherein the airfoil structure includes an airfoil member and a tuned mass damper, and the method includes: constructing a continuous state space equation of the airfoil structure based on the structural parameters of the airfoil structure; constructing a continuous state space equation of the aerodynamic system based on system identification; constructing a state space analysis model of a coupled system based on the continuous state space equation of the airfoil structure and the continuous state space equation of the aerodynamic system; and evaluating the stall flutter stability of the airfoil structure based on the state space analysis model of the coupled system. The present application comprehensively considers the structural response and aerodynamic characteristics, establishes a state space analysis model of a coupled system, and can accurately evaluate the stall flutter stability of the airfoil structure, thereby providing accurate data support for the optimal design of the airfoil structure, effectively ensuring the safety of the airfoil structure during operation, and reducing personal and property losses.

[0028] See attached Figure 1 , Figure 1 FIG. 1 is a flow chart of the main steps of a method for evaluating stall flutter stability of an airfoil structure according to an embodiment of the present application. Figure 1 As shown, in the embodiment of the present application, the airfoil structure includes an airfoil member and a tuned mass damper, and the airfoil structure stall flutter stability assessment method mainly includes the following steps S101 to S104.

[0029] Step S101: constructing a continuous state space equation of the airfoil structure based on the structural parameters of the airfoil structure.

[0030] In this embodiment, the airfoil structure refers to an airfoil equipped with a tuned mass damper, and the airfoil may be a wind turbine blade, an aircraft wing, or other structure. A tuned mass damper (TMD) is a vibration control device that is widely used in structures such as buildings and bridges. The working principle of a tuned mass damper is to effectively absorb and suppress the vibration of the main structure by adding a secondary system with specific mass, stiffness, and damping to the main structure.

[0031] Step S102: Based on system identification, construct a continuous state space equation of the aerodynamic system.

[0032] In this embodiment, based on system identification and according to the observed system input and output data, a linear autoregressive model with eXogenous input (ARX) is adopted to represent the output of the system as a linear superposition of the input and output of the previous several steps of the system, thereby constructing the continuous state space equation of the aerodynamic system.

[0033] Step S103: constructing a state space analysis model of the coupling system based on the continuous state space equation of the airfoil structure and the continuous state space equation of the aerodynamic system;

[0034] Step S104: evaluating the stall flutter stability of the airfoil structure based on the state space analysis model of the coupled system.

[0035] Based on the methods described in steps S101 to S104 above, the present application couples the continuous state-space equations of the airfoil structure with the continuous state-space equations of the aerodynamic system to construct a state-space analysis model, which comprehensively considers the influence of the dynamic characteristics of the structure and the aerodynamic effects, and can be closer to the actual working conditions, thereby truly reflecting the dynamic behavior of the airfoil in actual operation, thereby improving the accuracy of the airfoil stall flutter stability assessment, and providing strong data support for the optimal design of the airfoil structure, thereby ensuring the safety of the airfoil structure during operation and reducing the risk of personal injury and property loss caused by structural instability or flutter.

[0036] The above steps S101 to S104 are further explained below.

[0037] With respect to step S101, in one embodiment, constructing the continuous state-space equation of the airfoil structure based on the structural parameters of the airfoil structure includes: establishing the structural motion equation of the airfoil structure based on the structural parameters of the airfoil structure; and constructing the continuous state-space equation of the airfoil structure based on the structural motion equation of the airfoil structure.

[0038] Specifically, for the airfoil structure with a tuned mass damper, the structural parameters of the airfoil and the tuned mass damper are comprehensively considered to establish the structural motion equation of the airfoil structure, and based on the structural motion equation of the airfoil structure, the continuous state space equation of the airfoil structure is constructed.

[0039] In one embodiment, the structural parameters of the airfoil structure include parameter information of the airfoil component and parameter information of a tuned mass damper; establishing the structural motion equation of the airfoil structure based on the structural parameters of the airfoil structure includes: establishing the structural motion equation of the airfoil structure based on the parameter information of the airfoil component and the parameter information of the tuned mass damper, wherein the parameter information of the airfoil component includes mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, flutter angular acceleration and aerodynamic force information, and the parameter information of the tuned mass damper includes mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity and flutter angular acceleration.

[0040] Specifically, the airfoil refers to an aircraft wing or a wind turbine blade, and its vertical section is assumed to be a two-dimensional airfoil. In this simplified model, the airfoil has only one rotational degree of freedom, that is, the airfoil can rotate around a fixed rotation center, and the structural motion system of the airfoil can be described by a mass-damper-spring system. The tuned mass damper consists of a mass block, a spring, and a damper. The installation center of the tuned mass damper is aligned with the rotation center of the airfoil, and the structural motion system of the two is consistent, which is also a mass-damper-spring system.

[0041] The motion model of the airfoil structure is as follows: Figure 2 As shown in the figure, the airfoil structure performs a single-degree-of-freedom pitch motion around the rotation center. There is the following corresponding relationship between the incoming flow angle of attack and the torsion angle and flutter angular displacement of the airfoil structure installation: α=θ0+θ1 (1)

[0042] Among them, θ0 is the torsion angle of the airfoil structure installation, θ1 is the flutter angular displacement of the airfoil structure, and α is the incoming flow angle of attack.

[0043] Based on the mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity, flutter angular acceleration and aerodynamic information of the airfoil, as well as the mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity and flutter angular acceleration of the tuned mass damper, the structural motion equation of the airfoil structure is constructed, wherein the aerodynamic information of the airfoil refers to the torque of the aerodynamic force on the airfoil structure. The structural motion equation of the airfoil structure is expressed as:

[0044] Where m1 is the mass of the airfoil, is the flutter angular acceleration of the airfoil, c1 is the damping of the airfoil, is the flutter angular velocity of the airfoil, k1 is the spring stiffness of the airfoil, θ1 is the flutter angular displacement of the airfoil, θ2 is the flutter angular displacement of the tuned mass damper, F is the torque of the aerodynamic force on the airfoil structure, m2 is the mass of the tuned mass damper, is the flutter angular acceleration of the tuned mass damper, c2 is the damping of the tuned mass damper, is the flutter angular acceleration of the tuned mass damper, and k2 is the spring stiffness of the tuned mass damper.

[0045] In one embodiment, the continuous state space equation of the airfoil structure is constructed 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; defining state variables, and using the state variables to convert the structural motion equation in differential form into a continuous state space equation.

[0046] Specifically, based on the flutter angular displacement of the airfoil and the tuned mass damper, the displacement matrix ξ is defined as:

[0047] The displacement matrix is ​​used to transform the structural motion equation of the airfoil structure into the structural motion equation in differential form. The structural motion equation in differential form is expressed as:

[0048] 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

[0049]

[0050] Defining state variables The state variables are used to transform the structural motion equation in differential form into a continuous state space equation, which is expressed as:

[0051] Where F(t) is the torque matrix, t is the continuous time, , C s =[E 0],D s =[0], where E is the unit matrix.

[0052] With respect to step S102, in one embodiment, the construction of the continuous state space equation of the aerodynamic system based on system identification includes: establishing a multi-input and multi-output autoregressive model based on system identification, wherein the input data of the autoregressive model is the flutter angular displacement of the airfoil structure, and the output data is the torque of the aerodynamic force on the airfoil structure; defining a state vector, and using the state vector to convert the autoregressive model into a discrete state space equation; performing a bilinear transformation on the discrete state space equation to obtain a continuous state space equation of the aerodynamic system.

[0053] Specifically, the linear autoregressive model with exogenous inputs (ARX) is a model that represents the system output as a linear superposition of the system inputs of several previous steps, the external inputs of several previous steps, and the external inputs at the current moment.

[0054] Based on the system identification method, the flutter angular displacement of the airfoil structure is taken as the input data, and the torque of the aerodynamic force on the airfoil structure is taken as the output data. A multi-input and multi-output autoregressive model is established. The autoregressive model is expressed as:

[0055] The u and y vectors represent the input and output of the system, respectively. The input is the flutter angular displacement, u = θ1; the output is the torque of the aerodynamic force on the airfoil structure, y a =F; na, nb are the delay orders of input and output respectively; A i , B i are all coefficient matrices to be identified; e is the identification error, which is a dimensionless value used to indicate the relative error between the predicted value and the actual value.

[0056] The least square method is used to obtain the parameters to be identified in the system, and the order of the reduced-order model is determined by the identification error e.

[0057] Where N is the total number of data points, y a (i) is the actual value of the i-th data point, is the predicted value or identification value of the i-th data point.

[0058] By designing a reasonable training signal, the input data is the angular displacement θ1 of the airfoil flutter, and the computational fluid dynamics (CFD) method is used to solve the response value, which is the torque F of the aerodynamic force on the airfoil structure.

[0059] Define the state vector, which is expressed as: x a (k) = [y a (k-1),…,y a (k-na),u(k-1),u(k-nb+1)] T

[0060] Using the state vector, the autoregressive model is transformed into the discrete state space equation of the aerodynamic system. The discrete state space equation of the aerodynamic system is expressed as:

[0061] Among them, the matrix A a , B a , C a , D a They correspond to the system matrix, control matrix, output matrix and transfer matrix of the pneumatic system, respectively, and represent the dynamic characteristics of the pneumatic force; k is the discrete moment; u(k) is the input of the system at the kth moment; y a (k) is the output of the pneumatic system at the kth moment;

[0062] Through bilinear transformation, the discrete state space equation is converted into the continuous state space equation of the aerodynamic system. The continuous state space equation of the aerodynamic system is expressed as:

[0063] Among them, x a is the state vector, t is the continuous time, u(t) is the input of the system at the tth time; y a (t) is the output of the pneumatic system at time t.

[0064] With respect to step S103, in one embodiment, constructing a state space analysis model of the coupled system based on the continuous state space equations of the airfoil structure and the continuous state space equations of the aerodynamic system includes: coupling the continuous state space equations of the airfoil structure and the continuous state space equations of the aerodynamic system to form a closed-loop feedback process, and obtaining the state space analysis model of the coupled system.

[0065] Specifically, the continuous state space equation of the airfoil structure and the continuous state space equation of the aerodynamic system are connected by mutual feedback to form a closed-loop feedback process, and the state space analysis model of the coupled system is obtained. The state space analysis model of the coupled system is expressed as:

[0066] Among them, x s (t) is the state variable of the structural system, x a (t) is the state vector of the aerodynamic system, A s is the system matrix of the structural system, B s is the control matrix of the structural system, C s is the output matrix of the structural system, B a is the control matrix of the aerodynamic system, C a is the output matrix of the pneumatic system, D a is the transfer matrix of the aerodynamic system, A a is the system matrix of the aerodynamic system.

[0067] With respect to step S104, in one embodiment, the evaluating the stall flutter stability of the airfoil structure based on the state-space analysis model of the coupling system includes: solving the matrix eigenvalues ​​of the state-space analysis model of the coupling system, the real part of the matrix eigenvalues ​​being the damping of the coupling system, and the imaginary part being the frequency of the coupling system; based on the matrix eigenvalues, evaluating the stall flutter stability of the airfoil structure to determine the stable state of the airfoil structure.

[0068] Specifically, in the state space, the stability analysis of the stall flutter of the coupled system can be transformed into a matrix eigenvalue problem to study the system state equation. The real and imaginary parts of the matrix eigenvalue represent the damping and frequency of the coupled system, respectively. By solving the matrix eigenvalue, the stall flutter stability of the airfoil structure can be evaluated based on its real and imaginary parts, thereby determining the stable state of the system.

[0069] Specifically, if the real part of the matrix eigenvalue is less than zero, the system has negative damping, which means that after the system is disturbed, the damping will cause the system to gradually return to its original equilibrium position, thus keeping the system stable.

[0070] If the real part of the matrix eigenvalue is greater than zero, the system has positive damping, which indicates that the system's damping is insufficient to resist external disturbances, causing the system structure to diverge and the system to become unstable.

[0071] If the real part of the matrix eigenvalue is equal to zero, it means that the damping of the system can just offset the external disturbance, so that the system neither diverges nor converges, but maintains in a critical stable equilibrium state.

[0072] In an embodiment of the present application, a system identification method is used to construct a continuous state space equation of the aerodynamic system using a linear autoregressive model (ARX) with external input. At the same time, based on the structural parameters of the airfoil structure, the motion equation of the airfoil structure is established and converted into a continuous state space equation. Finally, the continuous state space equation of the aerodynamic system is coupled with the continuous state space equation of the airfoil structure to form an overall coupled system state space model. Then, an eigenvalue analysis is performed on the coupled system state space model, and the stability of the system is evaluated based on the real and imaginary parts of the matrix eigenvalues, providing a reliable reference for the stability analysis of the stall flutter of the airfoil structure.

[0073] See attached Figure 3 , Figure 3 FIG. 1 is a schematic flow chart of the main steps of a system for evaluating stall flutter stability of an airfoil structure according to another embodiment of the present application. Figure 3 As shown, in this embodiment, the structural motion equation of the airfoil structure is established through the structural dynamics system, and the continuous state space equation of the airfoil structure is determined based on the structural motion equation.

[0074] Reasonable training signals are designed through the fluid dynamics system as the basis for subsequent system identification. Based on the training signals, the autoregressive model (ARX) is used for system identification to determine the input-output relationship of the system. Discrete difference equations are used to simplify the description of the aerodynamic system and reduce the complexity of the model. The dynamic behavior of the aerodynamic system is represented by discrete state space equations. The discrete state space equations are converted into continuous state space equations for the aerodynamic system.

[0075] Then, the continuous state-space equations of the aerodynamic system and the structural dynamics system are coupled to form a state-space analysis model of the coupled system. The eigenvalue analysis of the state-space analysis model of the coupled system is then performed, and the stall flutter stability of the airfoil structure is evaluated based on the matrix eigenvalue.

[0076] 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.

[0077] 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.

[0078] Another aspect of the present application provides an airfoil structure stall flutter stability assessment system.

[0079] See attached Figure 4 , Figure 4 FIG. 1 is a schematic diagram of the main structure of a system for evaluating stall flutter stability of an airfoil structure according to an embodiment of the present application. Figure 4 As shown, the airfoil structure stall flutter stability assessment system in the embodiment of the present application mainly includes a first building module 41, a second building module 42, a third building module 43, and an assessment module 44. In some embodiments, one or more of the first building module 41, the second building module 42, the third building module 43, and the assessment module 44 can be combined into one module.

[0080] In some embodiments, the first construction module 41 can be configured to construct a continuous state space equation of the airfoil structure based on the structural parameters of the airfoil structure. The second construction module 42 can be configured to construct a continuous state space equation of the aerodynamic system based on system identification. The third construction module 43 can be configured to construct a state space analysis model of the coupled system based on the continuous state space equation of the airfoil structure and the continuous state space equation of the aerodynamic system. The evaluation module 44 can be configured to evaluate the stall flutter stability of the airfoil structure based on the state space analysis model of the coupled system. In one embodiment, the description of the specific implementation function can be found in steps S101 to S104.

[0081] The stall flutter stability evaluation system of the airfoil structure is used to perform Figure 1The embodiments of the stall flutter stability assessment method for airfoil structures shown in the figure are similar in 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 stability assessment system for airfoil structures can refer to the contents described in the embodiments of the stall flutter stability assessment method for airfoil structures, which will not be repeated here.

[0082] Another aspect of the present application provides an electronic device.

[0083] 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 in communication; 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 of the above embodiments is implemented. The electronic device described in the present application may include a driving device, a smart car, a robot, and the like. Figure 5 , Figure 5 FIG. 4 exemplarily shows that the memory 11 and the processor 12 are communicatively connected via a bus.

[0084] Another aspect of the present application also provides a computer-readable storage medium.

[0085] 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 stability assessment 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 stability assessment 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-temporary computer-readable storage medium.

[0086] 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 evaluating stall flutter stability of an airfoil structure, characterized in that: The airfoil structure comprises an airfoil and a tuned mass damper, and the method comprises: Based on the structural parameters of the airfoil structure, the continuous state space equation of the airfoil structure is constructed; Based on system identification, the continuous state space equation of the aerodynamic system is constructed; Based on the continuous state-space equation of the airfoil structure and the continuous state-space equation of the aerodynamic system, a state-space analysis model of the coupling system is constructed; The stall flutter stability of the airfoil structure is evaluated based on a state space analysis model of the coupled system.

2. The method for evaluating stall flutter stability of an airfoil structure according to claim 1, characterized in that: The continuous state space equation of the airfoil structure is constructed based on the structural parameters of the airfoil structure, including: Based on the structural parameters of the airfoil structure, a structural motion equation of the airfoil structure is established; Based on the structural motion equation of the airfoil structure, a continuous state space equation of the airfoil structure is constructed.

3. The method for evaluating stall flutter stability of an airfoil structure according to claim 2, characterized in that: The structural parameters of the airfoil structure include parameter information of the airfoil and parameter information of the tuned mass damper; The step of establishing a structural motion equation of the airfoil structure based on the structural parameters of the airfoil structure comprises: Based on the parameter information of the airfoil and the parameter information of the tuned mass damper, the structural motion equation of the airfoil structure 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, and the parameter information of the tuned mass damper includes mass, damping, spring stiffness, flutter angular displacement, flutter angular velocity and flutter angular acceleration.

4. The method for evaluating stall flutter stability of an airfoil structure according to claim 2, characterized in that: The continuous state space equation of the airfoil structure is constructed 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; State variables are defined, and the differential form of the structural motion equation is converted into a continuous state space equation using the state variables.

5. The method for evaluating stall flutter stability of an airfoil structure according to claim 1, characterized in that: The method of constructing the continuous state space equation of the aerodynamic system based on system identification includes: Based on system identification, a multi-input and multi-output autoregressive model is established, wherein the input data of the autoregressive model is the flutter angular displacement of the airfoil structure, and the output data is the torque of the aerodynamic force on the airfoil structure; defining a state vector, and using the state vector to transform the autoregressive model into a discrete state space equation; The discrete state space equation is bilinearly transformed to obtain the continuous state space equation of the aerodynamic system.

6. The method for evaluating stall flutter stability of an airfoil structure according to claim 1, characterized in that: The state space analysis model of the coupled system is constructed based on the continuous state space equation of the airfoil structure and the continuous state space equation of the aerodynamic system, including: The continuous state space equation of the airfoil structure and the continuous state space equation of the aerodynamic system are coupled to form a closed-loop feedback process, and a state space analysis model of the coupled system is obtained.

7. The method for evaluating stall flutter stability of an airfoil structure according to claim 1, characterized in that: The evaluating the stall flutter stability of the airfoil structure based on the state space analysis model of the coupled system comprises: Solving the matrix eigenvalue of the state space analysis model of the coupling system, the real part of the matrix eigenvalue is the damping of the coupling system, and the imaginary part is the frequency of the coupling system; Based on the matrix eigenvalues, the stall flutter stability of the airfoil structure is evaluated to determine the stable state of the airfoil structure.

8. A stall flutter stability assessment system for an airfoil structure, characterized in that: The airfoil structure includes an airfoil and a tuned mass damper, and the system includes: A first building module is used to build a continuous state space equation of the airfoil structure based on the structural parameters of the airfoil structure; The second building module is used to build the continuous state space equations of the aerodynamic system based on system identification; A third building module is used to build a state space analysis model of the coupling system based on the continuous state space equation of the airfoil structure and the continuous state space equation of the aerodynamic system; An evaluation module is used to evaluate the stall flutter stability of the airfoil structure based on a state space analysis model of the coupled system.

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 airfoil structure stall flutter stability assessment method 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 airfoil structure stall flutter stability assessment method according to any one of claims 1 to 7.

Images