An angle of attack adjusting method, device, medium and product of a dynamic stall test device
By acquiring and normalizing the dimensional data of the dynamic stall test device and using the sequential quadratic programming algorithm to optimize the lengths of the crank, connecting rod and rocker, the problems of small adjustment range and insufficient precision of the traditional device were solved, and higher-precision angle of attack adjustment was achieved.
Patent Information
- Application Number
- CN202410965612.8
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-17
- Publication Date
- 2025-10-17
- Estimated Expiration
- 2044-07-17
AI Technical Summary
The angle of attack adjustment range of traditional dynamic stall test equipment is small and the adjustment accuracy is insufficient.
By obtaining the current dimensional data of the angle of attack adjustment mechanism of the dynamic stall test device and the angle between the line connecting the frame connection points and the horizontal line, and normalizing them, the sequential quadratic programming algorithm is used to solve the optimization model to determine the optimal crank, connecting rod and rocker lengths to adjust the airfoil angle of attack.
The accuracy and range of angle of attack adjustment are improved, and the difference from the expected value is reduced.
Smart Images
Figure CN118916571B_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The application relates to the angle of attack adjustment field of a dynamic stall test device, in particular to a dynamic stall test device angle of attack adjustment method, equipment, medium and product. BACKGROUND
[0002] A traditional dynamic stall test device realizes the cosine law change of the airfoil angle of attack by changing the crank length and the connecting rod length in a crank rocker mechanism. The average angle of attack is related to the connecting rod length, and the amplitude of the angle of attack is related to the crank length, and the two are not coupled. Therefore, the scheme is widely used in the early dynamic stall test. However, the effective adjustment range of the traditional scheme is small, and the adjustment precision is insufficient. SUMMARY
[0003] The purpose of the application is to provide a dynamic stall test device angle of attack adjustment method, equipment, medium and product to improve the angle of attack adjustment precision and adjustment range.
[0004] To achieve the above purpose, the application provides the following scheme:
[0005] In a first aspect, the application provides a dynamic stall test device angle of attack adjustment method, comprising:
[0006] obtaining current size data of a dynamic stall test device angle of attack adjustment mechanism and an included angle between a rack connection point line and a horizontal line; the size data includes a crank length, a connecting rod length, a rocker length and a rack length;
[0007] normalizing the current size data by the rack length to obtain processed size data;
[0008] based on the processed size data, using a sequential quadratic programming algorithm to solve an optimization model to determine optimal crank length, optimal connecting rod length and optimal rocker length; wherein the optimization model includes an objective function and a constraint condition; the objective function is an equation related to the correlation coefficient of the actual value and the expected value of the airfoil angle of attack, the airfoil angular velocity and the airfoil angular acceleration; the constraint condition includes a rod length constraint condition and a motion law constraint condition; the rod length constraint condition is that the crank length is less than or equal to the connecting rod length, the rocker length and the rack length, and the sum of the crank length and the connecting rod length is less than or equal to the sum of the rocker length and the rack length, the sum of the crank length and the rocker length is less than or equal to the sum of the connecting rod length and the rack length, and the sum of the crank length and the rack length is less than or equal to the sum of the connecting rod length and the rocker length; the motion law constraint condition is that the average value of the actual value of the airfoil angle of attack is equal to the expected average angle of attack, and the amplitude of the actual value of the airfoil angle of attack is equal to the expected angle of attack amplitude;
[0009] According to the optimal crank length, the optimal connecting rod length, the optimal rocker length and the included angle between the rack connecting point line and the horizontal line, an optimal attack angle is determined to adjust the airfoil attack angle.
[0010] Optionally, based on the processed size data, the optimal crank length, the optimal connecting rod length and the optimal rocker length are determined by solving the optimization model using a sequential quadratic programming algorithm, specifically including:
[0011] According to the processed size data, an airfoil attack angle actual value, an airfoil angular velocity actual value and an airfoil angular acceleration actual value are determined.
[0012] Based on the airfoil attack angle actual value, the airfoil angular velocity actual value, the airfoil angular acceleration actual value, an airfoil attack angle expected value, an airfoil angular velocity expected value and an airfoil angular acceleration expected value, the optimal crank length, the optimal connecting rod length and the optimal rocker length are determined by solving the optimization model using a sequential quadratic programming algorithm.
[0013] Optionally, according to the processed size data, an airfoil attack angle actual value is determined, specifically including:
[0014] The rocker rotation angle actual value is determined by the formula
[0015] The airfoil attack angle actual value is determined by the formula α = π - Ψ - δ.
[0016] Wherein, α is the airfoil attack angle actual value; Ψ is the rocker rotation angle actual value; δ is the included angle between the rack connecting point line and the horizontal line; a * is the processed crank length; c * is the processed rocker length; θ is the rotation angle of the crank; K, f are intermediate variables, K 2 = 1 + a *2 + c *2 - b *2 , f 2 = 1 + a *2 - 2a * cos θ, b * is the processed connecting rod length.
[0017] Optionally, according to the processed size data, an airfoil angular velocity actual value is determined, specifically including:
[0018] The rocker angular velocity actual value is determined by the formula , and the airfoil angular velocity actual value is determined by the formula
[0019] Wherein, is the airfoil angular velocity actual value; is the rocker angular velocity actual value; a* is the processed crank length; θ is the rotation angle of the crank; M, f are intermediate variables, M 2 = K 2 - 2a*cosθ, f 2 = 1 + a *2 - 2a * cosθ, K is an intermediate variable, K 2 = 1 + a *2 + c *2 - b *2 .
[0020] Optionally, according to the processed size data, the wing type angle acceleration actual value is determined, specifically comprising:
[0021] The remote lever angle acceleration actual value is determined by using the formula The wing type angle acceleration actual value is determined by using the formula
[0022]
[0023] wherein, is the wing type angle acceleration actual value; is the remote lever angle acceleration actual value; a * is the processed crank length; θ is the rotation angle of the crank; M, f, S are intermediate variables, M 2 = K 2 - 2a*cosθ, K is an intermediate variable, K 2 = 1 + a *2 + c *2 - b *2 , f 2 = 1 + a *2 - 2a * cosθ, c * is the processed rocker length.
[0024] Optionally, the target function is:
[0025]
[0026] wherein, f(X) is the target function; X is the processed size data; X = [a / d, b / d, c / d] = [a * , b * , c * ]; R α is the correlation coefficient of the wing type angle actual value and the expected value; is the correlation coefficient of the wing type angle velocity actual value and the expected value; is the correlation coefficient of the wing type angle acceleration actual value and the expected value.
[0027] Optionally, the rod length constraint condition is:
[0028]
[0029] wherein a * is the processed crank length; b * is the processed connecting rod length; c * is the processed rocker length;
[0030] The motion law constraint condition is:
[0031]
[0032] wherein α m is the expected average angle of attack; α a is the expected angle of attack amplitude; α max is the maximum value of the actual value of the airfoil angle of attack; α min is the minimum value of the actual value of the airfoil angle of attack.
[0033] In a second aspect, the present application provides a computer device, comprising: a memory, a processor to store a computer program on the memory and run the computer program on the processor, and the processor executes the computer program to implement the angle of attack adjustment method of the dynamic stall test device according to any one of the above.
[0034] In a third aspect, the present application provides a computer readable storage medium, which stores a computer program, and the computer program is executed by a processor to implement the angle of attack adjustment method of the dynamic stall test device according to any one of the above.
[0035] In a fourth aspect, the present application provides a computer program product, which comprises a computer program, and the computer program is executed by a processor to implement the angle of attack adjustment method of the dynamic stall test device according to any one of the above.
[0036] According to the embodiments provided in the present application, the following technical effects are disclosed:
[0037] The present application provides a method, device, medium, and product for adjusting the angle of attack of a dynamic stall test device. The method comprises obtaining the current dimensional data of the angle of attack adjustment mechanism of the dynamic stall test device and the angle between the line connecting the frame connection points and the horizontal line; normalizing the current dimensional data by the frame length to obtain processed dimensional data; and solving an optimization model based on the processed dimensional data using a sequential quadratic programming algorithm to determine the optimal crank length, optimal connecting rod length, and optimal rocker length. The optimization model includes an objective function and constraints. The objective function is an equation for the correlation coefficient between the actual and expected values of the airfoil angle of attack, airfoil angular velocity, and airfoil angular acceleration. The constraints include rod length constraints and motion law constraints. The optimal angle of attack is determined based on the optimal rod length of each rod and the angle between the line connecting the frame connection points and the horizontal line to adjust the airfoil angle of attack. The present application improves the accuracy and adjustment range of angle of attack adjustment. BRIEF DESCRIPTION OF THE DRAWINGS
[0038] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.
[0039] Figure 1 A schematic flow chart of a method for adjusting the angle of attack of a dynamic stall test device provided in one embodiment of the present application;
[0040] Figure 2 This is a schematic diagram of the angle of attack adjustment mechanism of the dynamic stall test device;
[0041] Figure 3 is α m =10°,α a =10° The comparison curve between the actual and expected values of the airfoil angle of attack under the two schemes;
[0042] Figure 4 is α m =10°,α a =10° error curve between the actual and expected values of the airfoil angle of attack under the two schemes;
[0043] Figure 5 is α m =10°,α a =10° The comparison curve between the actual and expected values of the airfoil angular velocity under the two schemes;
[0044] Figure 6 is α m =10°,α a =10° error curves between the actual and expected values of the airfoil angular velocity under the two schemes;
[0045] Figure 7 for α m = 10°, α a = 10° Actual and expected wing angle acceleration comparison curve diagram under two schemes;
[0046] Figure 8 for α m = 10°, α a = 10° Actual and expected wing angle acceleration error curve diagram under two schemes;
[0047] Figure 9 for α m = 20°, α a = 10° Actual and expected wing angle of attack comparison curve diagram under two schemes;
[0048] Figure 10 for α m = 20°, α a = 10° Actual and expected wing angle of attack error curve diagram under two schemes;
[0049] Figure 11 for α m = 20°, α a = 10° Actual and expected wing angular velocity comparison curve diagram under two schemes;
[0050] Figure 12 for α m = 20°, α a = 10° Actual and expected wing angular velocity error curve diagram under two schemes;
[0051] Figure 13 for α m = 20°, α a = 10° Actual and expected wing angle acceleration comparison curve diagram under two schemes;
[0052] Figure 14 for α m = 20°, α a = 10° Actual and expected wing angle acceleration error curve diagram under two schemes;
[0053] Figure 15 for α m = 10°, α a = 20° Actual and expected wing angle of attack comparison curve diagram under two schemes;
[0054] Figure 16 for α m = 10°, α a = 20° Actual and expected wing angle of attack error curve diagram under two schemes;
[0055] Figure 17 for α m = 10°, α a = 20° two schemes under the wing angle velocity actual value and the expected value of the comparison chart;
[0056] Figure 18 for α m = 10°, α a = 20° two schemes under the wing angle velocity actual value and the expected value error chart;
[0057] Figure 19 for α m = 10°, α a = 20° two schemes under the wing angle acceleration actual value and the expected value of the comparison chart;
[0058] Figure 20 for α m = 10°, α a = 20° two schemes under the wing angle acceleration actual value and the expected value error chart;
[0059] Figure 21 is a structural schematic diagram of a computer device provided by an embodiment of the present application. DETAILED DESCRIPTION
[0060] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.
[0061] The above purposes, features and advantages of the present application can be more obvious and easy to understand. The present application will be further described in detail below with reference to the drawings and specific embodiments.
[0062] In an exemplary embodiment, as shown in Figure 1 a dynamic stall test device angle of attack adjustment method is provided, comprising:
[0063] S1: obtaining the current size data of the dynamic stall test device angle of attack adjustment mechanism and the angle between the rack connection point connecting line and the horizontal line; the size data includes crank length, connecting rod length, rocker length and rack length.
[0064] In practical application, the dynamic stall test device angle of attack adjustment mechanism is simplified as shown in Figure 2The motion diagram shows that the lengths of the rods are: crank length AB = a, connecting rod length BC = b, rocker length CD = c, and rack connection point connecting line length DA = d. θ is the rotation angle of the crank (driving input member), Ψ is the rotation angle of the rocker (driven output member), and the angle α between the rocker and the horizontal plane is the wing type attack angle. A and D are the rack connection points of the test device, and the connecting line has a fixed angle δ = 50° with the horizontal line.
[0065] S2: normalizing the current size data by the rack length to obtain processed size data.
[0066] In actual application, when the lengths of the rods of the crank-rocker mechanism are enlarged or reduced by the same proportion, the motion law of the rocker remains unchanged. Therefore, the lengths of the rods are also normalized by the rack length d in the optimization process. The design variables are:
[0067] X = [a / d, b / d, c / d] = [a * ,b * ,c * ].
[0068] The expected sine and cosine motion law is:
[0069] α = α m + α a cos(ωt).
[0070] In the formula, α m is the expected average attack angle, α a is the expected attack angle amplitude, and ω is the circular frequency of oscillation.
[0071] S3: based on the processed size data, the sequence quadratic programming algorithm is used to solve the optimization model to determine the optimal crank length, the optimal connecting rod length, and the optimal rocker length; wherein the optimization model includes a target function and a constraint condition; the target function is an equation related to the correlation coefficient of the actual value and the expected value of the wing type attack angle, the wing type angular velocity, and the wing type angular acceleration; the constraint condition includes a rod length constraint condition and a motion law constraint condition; the rod length constraint condition is that the crank length is less than or equal to the connecting rod length, the rocker length, and the rack length, and the sum of the crank length and the connecting rod length is less than or equal to the sum of the rocker length and the rack length, the sum of the crank length and the rocker length is less than or equal to the sum of the connecting rod length and the rack length, and the sum of the crank length and the rack length is less than or equal to the sum of the connecting rod length and the rocker length; the motion law constraint condition is that the average value of the actual value of the wing type attack angle is equal to the expected average attack angle, and the amplitude of the actual value of the wing type attack angle is equal to the expected attack angle amplitude.
[0072] As an optional implementation, S3 specifically includes:
[0073] S31: determining an actual value of an airfoil angle of attack, an actual value of an airfoil angular velocity and an actual value of an airfoil angular acceleration according to the processed size data.
[0074] According to the processed size data, the actual value of the airfoil angle of attack is determined, specifically comprising:
[0075] The actual value of the rocker angle is determined by using the formula .
[0076] The actual value of the airfoil angle of attack is determined by using the formula α=π-Ψ-δ.
[0077] Wherein, α is the actual value of the airfoil angle of attack; Ψ is the actual value of the rocker angle; δ is the angle between the connecting line of the rack connecting point and the horizontal line; a * is the processed length of the crank; c * is the processed length of the rocker; θ is the rotation angle of the crank; K, f are intermediate variables, K 2 =1+a *2 +c *2 -b *2 , f 2 =1+a *2 -2a * cosθ, b * is the processed length of the connecting rod.
[0078] According to the processed size data, the actual value of the airfoil angular velocity is determined, specifically comprising:
[0079] The actual value of the rocker angular velocity is determined by using the formula , and then the actual value of the airfoil angular velocity is determined by using the formula .
[0080] Wherein, is the actual value of the airfoil angular velocity; is the actual value of the rocker angular velocity; M is an intermediate variable, M 2 =K 2 -2a*cosθ.
[0081] According to the processed size data, the actual value of the airfoil angular acceleration is determined, specifically comprising:
[0082] The actual value of the rocker angular acceleration is determined by using the formula .
[0083] The actual value of the airfoil angular acceleration is determined by using the formula .
[0084] Wherein, is the actual value of the airfoil angular acceleration; is the actual value of the rocker angular acceleration; S is an intermediate variable,
[0085] S32: Based on the airfoil angle of attack actual value, the airfoil angular velocity actual value, the airfoil angular acceleration actual value, the airfoil angle of attack expected value, the airfoil angular velocity expected value and the airfoil angular acceleration expected value, the optimization model is solved by using a sequential quadratic programming algorithm to determine the optimal crank length, the optimal connecting rod length and the optimal rocker length. In actual application, the sequential quadratic programming (SQP) algorithm is used to obtain the rod length under the optimal condition and the corresponding actual output value.
[0086] In actual application, the correlation coefficient of the airfoil expected angle of attack, angular velocity or angular acceleration of each phase and the corresponding actual turning angle, angular velocity or angular acceleration is defined as follows:
[0087]
[0088] In the formula, cov(·) and σ respectively represent the covariance function and the standard deviation function.t i is the airfoil angle of attack expected value, the airfoil angular velocity expected value or the airfoil angular acceleration expected value; p i is the airfoil angle of attack actual value, the airfoil angular velocity actual value or the airfoil angular acceleration actual value, and are the average values of t and p, respectively.
[0089] The weight combination of the correlation coefficient of the actual value and the expected value of the airfoil angle of attack, angular velocity and angular acceleration is taken as a target function, and the target function is:
[0090]
[0091] Wherein, f(X) is the target function; X=[a / d, b / d, c / d]=[a * ,b * ,c * ]; R Ψ is the correlation coefficient of the airfoil angle of attack actual value and the expected value; is the correlation coefficient of the airfoil angular velocity actual value and the expected value; is the correlation coefficient of the airfoil angular acceleration actual value and the expected value.
[0092] In actual application, the constraint conditions include two types: rod length constraint condition and motion law constraint condition.
[0093] The rod length satisfies the following relationship: the crank length is less than or equal to the length of the remaining three rods, and the sum of the crank length and the length of any rod is less than or equal to the sum of the lengths of the other two rods.
[0094] The motion law satisfies the following relationship: the average value and amplitude of the actual value of the airfoil angle of attack are equal to the average value and amplitude of the expected cosine motion, respectively. The average value and amplitude of the actual value of the airfoil angle of attack are determined by the maximum value and minimum value of the actual value of the airfoil angle of attack, which are defined as follows:
[0095]
[0096] As an optional implementation, the rod length constraint condition is:
[0097]
[0098] wherein a * is the processed crank length; b * is the processed connecting rod length; and c * is the processed rocker length.
[0099] The motion law constraint condition is:
[0100]
[0101] wherein α m is the expected average angle of attack; α a is the expected amplitude of the angle of attack; α max is the maximum value of the actual value of the airfoil angle of attack; and α min is the minimum value of the actual value of the airfoil angle of attack.
[0102] S4: determining an optimal angle of attack according to the optimal crank length, the optimal connecting rod length, the optimal rocker length, and the angle between the connecting line of the rack connection point and the horizontal line, to adjust the airfoil angle of attack.
[0103] For different dynamic stall test states of average angle of attack and amplitude of angle of attack, the corresponding rod lengths of the dynamic stall test device are obtained by using the traditional scheme and the improved scheme, respectively, as shown in Table 1, wherein the traditional scheme c / d=0.600.
[0104] Table 1: Statistics of rod lengths of dynamic stall test devices obtained by using traditional scheme and improved scheme
[0105]
[0106] A non-dimensional error (NE) is defined to represent the difference between the two schemes and the expected output value:
[0107] NE=|(p i -t i ) / (t max -t min )| i＝0...n.
[0108] Figures 3-20 The actual value and error of the angle of attack, angular velocity and angular acceleration of the airfoil in two cycles under two schemes are compared with the expected value under the three test states respectively. Figures 3-20 It can be seen from the comparison that the difference between the improved scheme and the expected value is significantly smaller than that of the traditional scheme due to the simultaneous change of the three bar lengths and the application of the optimization method.
[0109] In an exemplary embodiment, a computer device, which can be a server or a terminal, is provided, and an internal structure diagram of the computer device can be as shown in Figure 21 The computer device includes a processor, a memory, an input / output interface (I / O) and a communication interface. The processor, the memory and the input / output interface are connected through a system bus, and the communication interface is connected to the system bus through the input / output interface. The processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store rod length data. The input / output interface of the computer device is used to exchange information between the processor and external devices. The communication interface of the computer device is used to communicate with external terminals through network connection. The computer program is executed by the processor to implement an angle of attack adjustment method for a dynamic stall test device.
[0110] Those skilled in the art can understand that Figure 21 the structure shown in the figure is only a block diagram of part of the structure related to the scheme of the present application, and does not constitute a limitation on the computer device to which the scheme of the present application is applied. The specific computer device can include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components.
[0111] In an exemplary embodiment, a computer device is also provided, including a memory and a processor, the memory storing a computer program, and the processor executing the computer program to implement the steps in the above method embodiments.
[0112] In an exemplary embodiment, a computer readable storage medium is provided, storing a computer program, which is executed by a processor to implement the steps in the above method embodiments.
[0113] In an exemplary embodiment, a computer program product is provided, including a computer program, which is executed by a processor to implement the steps in the above method embodiments.
[0114] It should be noted that the user information (including but not limited to user equipment information, user personal information, etc.) and data (including but not limited to data for analysis, stored data, displayed data, etc.) involved in the present application are all information and data authorized by the user or authorized by all parties, and the collection, use and processing of related data need to comply with relevant regulations.
[0115] It can be understood by those skilled in the art that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing related hardware through a computer program. The computer program can be stored in a non-volatile computer readable storage medium. When the computer program is executed, it can include the processes of the above-mentioned embodiments of each method. Any reference to memory, database or other medium used in each embodiment provided by the present application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (Read-Only Memory, ROM), magnetic tape, floppy disk, flash memory, optical storage, high-density embedded non-volatile memory, resistive memory (ReRAM), magnetoresistive random access memory (Magnetoresistive Random Access Memory, MRAM), ferroelectric memory (Ferroelectric Random Access Memory, FRAM), phase change memory (Phase Change Memory, PCM), graphene memory, etc. Volatile memory can include random access memory (Random Access Memory, RAM) or external cache memory, etc. As an illustration but not limitation, RAM can be in various forms, such as static random access memory (Static Random Access Memory, SRAM) or dynamic random access memory (Dynamic Random Access Memory, DRAM), etc.
[0116] The database involved in each embodiment provided by the present application can include at least one of a relational database and a non-relational database. The non-relational database can include a distributed database based on a block chain, etc., without being limited thereto. The processor involved in each embodiment provided by the present application can be a general-purpose processor, a central processing unit, a graphics processing unit, a digital signal processor, a programmable logic device, a data processing logic device based on quantum computing, etc., without being limited thereto.
[0117] Any technical features in the above embodiments can be combined, and for the sake of brevity, not all possible combinations are described above, however, it should be understood that the application encompasses all possible combinations of the technical features unless such a combination is not technically possible.
[0118] The principles and implementation manners of the present application are described herein by using specific examples, and the above embodiments are only used to help understand the method of the present application and its core idea; meanwhile, according to the idea of the present application, the specific implementation manners and application scopes will be changed by those skilled in the art. In conclusion, the content of the present specification should not be understood as a limitation of the present application.
Claims
1. A method for adjusting the angle of attack of a dynamic stall test device, characterized in that: include: Obtaining current dimensional data of the angle of attack adjustment mechanism of the dynamic stall test device and the angle between the line connecting the frame connection points and the horizontal line; the dimensional data includes crank length, connecting rod length, rocker length and frame length; Normalizing the current size data by the rack length to obtain processed size data; Based on the processed dimensional data, the sequential quadratic programming algorithm is used to solve the optimization model to determine the optimal crank length, optimal connecting rod length and optimal rocker length; wherein, the optimization model includes an objective function and constraints; the objective function is an equation of the correlation coefficient between the actual value and the expected value of the airfoil angle of attack, the airfoil angular velocity and the airfoil angular acceleration; the constraints include a rod length constraint and a motion law constraint; the rod length constraint is that the crank length is less than or equal to the connecting rod length, the rocker length and the frame length, and the sum of the crank length and the connecting rod length is less than or equal to the sum of the rocker length and the frame length, the sum of the crank length and the rocker length is less than or equal to the sum of the connecting rod length and the frame length, and the sum of the crank length and the frame length is less than or equal to the sum of the connecting rod length and the rocker length; the motion law constraint is that the average value of the actual value of the airfoil angle of attack is equal to the expected average angle of attack, and the amplitude of the actual value of the airfoil angle of attack is equal to the amplitude of the expected angle of attack; An optimal angle of attack is determined based on the optimal crank length, the optimal connecting rod length, the optimal rocker length, and the angle between the line connecting the frame connection points and the horizontal line to adjust the airfoil angle of attack.
2. The method for adjusting the angle of attack of a dynamic stall test device according to claim 1, characterized in that: Based on the processed dimensional data, the sequential quadratic programming algorithm is used to solve the optimization model to determine the optimal crank length, optimal connecting rod length, and optimal rocker length, including: Determining an actual value of the airfoil angle of attack, an actual value of the airfoil angular velocity, and an actual value of the airfoil angular acceleration based on the processed dimensional data; Based on the actual value of the airfoil angle of attack, the actual value of the airfoil angular velocity, the actual value of the airfoil angular acceleration, the expected value of the airfoil angle of attack, the expected value of the airfoil angular velocity and the expected value of the airfoil angular acceleration, a sequential quadratic programming algorithm is used to solve the optimization model to determine the optimal crank length, the optimal connecting rod length and the optimal rocker length.
3. The method for adjusting the angle of attack of a dynamic stall test device according to claim 2, characterized in that: Determining the actual value of the airfoil angle of attack based on the processed dimensional data specifically includes: Using the formula Determine the actual value of the joystick angle; Use the formula α=π-Ψ-δ to determine the actual value of the airfoil angle of attack; Among them, α is the actual value of the airfoil angle of attack; Ψ is the actual value of the rocker angle; δ is the angle between the line connecting the frame connection points and the horizontal line; a * is the crank length after processing; c * is the length of the rocker after processing; θ is the angle of the crank; K and f are intermediate variables, K 2 =1+a *2 +c *2 -b *2 , f 2 =1+a *2 -2a * cosθ,b * is the length of the connecting rod after processing.
4. The method for adjusting the angle of attack of a dynamic stall test device according to claim 3, characterized in that: Determining the actual value of the airfoil angular velocity based on the processed dimensional data specifically includes: Using the formula Determine the actual value of the joystick angular velocity and then use the formula Determine the actual value of the airfoil angular velocity; in, is the actual value of the airfoil angular velocity; is the actual value of the joystick angular velocity; a * is the crank length after processing; θ is the crank angle; M and f are intermediate variables, M 2 =K 2 -2a*cosθ,f 2 =1+a *2 -2a * cosθ, K is the intermediate variable, K 2 =1+a *2 +c *2 -b *2 .
5. The method for adjusting the angle of attack of a dynamic stall test device according to claim 3, characterized in that: Determining the actual value of the airfoil angular acceleration based on the processed dimensional data specifically includes: Using the formula Determine the actual value of the remote stick angular acceleration; Using the formula Determine the actual value of the airfoil angular acceleration; in, is the actual value of the airfoil angular acceleration; is the actual value of the remote stick angular acceleration; a * is the crank length after processing; θ is the crank angle; M, f, S are intermediate variables, M 2 =K 2 -2a*cosθ, K is the intermediate variable, K 2 =1+a *2 +c *2 -b *2 , f 2 =1+a *2 -2a * cosθ, c * is the length of the rocker after processing.
6. The method for adjusting the angle of attack of a dynamic stall test device according to claim 3, characterized in that: The objective function is: Where f(X) is the objective function; X is the processed size data; X = [a / d, b / d, c / d] = [a * ,b * ,c * ]; a is the crank length; b is the connecting rod length; c is the rocker length; d is the length of the line connecting the frame connection points; R α is the correlation coefficient between the actual value and the expected value of the airfoil angle of attack; is the correlation coefficient between the actual value and the expected value of the airfoil angular velocity; is the correlation coefficient between the actual value and the expected value of the airfoil angular acceleration.
7. The method for adjusting the angle of attack of a dynamic stall test device according to claim 1, characterized in that: The rod length constraint condition is: Among them, a * is the crank length after processing; b * is the length of the connecting rod after processing; c * is the length of the rocker after processing; The motion law constraints are: Among them, α m is the expected average angle of attack; α a is the expected angle of attack amplitude; α max is the maximum value of the actual value of the airfoil angle of attack; α min is the minimum actual value of the airfoil angle of attack.
8. A computer device comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the angle of attack adjustment method for a dynamic stall test device according to any one of claims 1 to 7.
9. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by a processor, the method for adjusting the angle of attack of a dynamic stall test device according to any one of claims 1 to 7 is implemented.
10. A computer program product comprising a computer program, characterized in that When the computer program is executed by a processor, the method for adjusting the angle of attack of a dynamic stall test device according to any one of claims 1 to 7 is implemented.