Aerodynamic Force Determination Method, Device, Electronic Device and Storage Medium

Abstract

The present invention provides a method, apparatus, electronic device and storage medium for determining aerodynamic force, relating to the technical field of cable-stayed bridges. The method includes: after the target rigid segment model reaches a steady state vibration, collecting target images of the target rigid segment model at multiple wind speeds; for each wind speed, determining the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the center positions of the first target circle and the second target circle in the target image; determining the vertical component force corresponding to the relative displacement time history according to the relative displacement time history and a preset conversion relationship between displacement and force; and obtaining the aerodynamic force of the target rigid segment model according to the vertical component force, the inertial force and the damping force of the target rigid segment model. That is, the solution of the present application avoids measuring the aerodynamic force using a high-precision dynamometer, thereby reducing the experimental cost and the installation difficulty of the experiment, and further improving the experimental efficiency.

Description

Technical Field

[0001] The present invention relates to the technical field of cable-stayed bridges, and in particular, to a method, device, electronic device and storage medium for determining aerodynamic forces. Background Art

[0002] The stay cable is the most important load-bearing component of a cable-stayed bridge, and its performance directly affects the overall safety of the bridge. Under the action of oncoming wind, the stay cable (also known as the stay) will cause periodic changes in the air pressure on the cable surface, and then generate periodic aerodynamic forces on the cable surface. When the frequency of the aerodynamic force is close to or equal to a certain natural vibration frequency of the cable, the cable will undergo vortex-induced resonance. This may lead to fatigue damage at the cable anchorage end, or damage the corrosion protection system at the cable end, shortening the service life of the cable. Therefore, calculating the generation mechanism of cable vortex-induced resonance, that is, calculating the aerodynamic force, is of great significance for the design and maintenance of cables.

[0003] Currently, the research method for cable vortex-induced resonance is to obtain the aerodynamic force of the cable rigid model using a high-precision force sensor in a wind tunnel test.

[0004] However, in a wind tunnel test, a high-precision force sensor not only has a high cost, but also is relatively complex to install in the experiment, resulting in low experimental efficiency. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to overcome the deficiencies of the prior art and provide a method, device, electronic device and storage medium for determining aerodynamic forces, so as to solve the problems in the prior art that in a wind tunnel test, a high-precision force sensor not only has a high cost, but also is relatively complex to install in the experiment, resulting in low experimental efficiency.

[0006] To solve the above technical problem, the technical solution proposed by the present invention is as follows:

[0007] In a first aspect, the present application provides a method for determining aerodynamic forces, the method comprising:

[0008] After the target rigid segment model reaches a steady state vibration, acquiring target images of the target rigid segment model at multiple wind speeds; wherein, the target of the target rigid segment model includes a first target circle, a second target circle and a cross mark, the cross mark is located at the center of the target, the distance between the center of the first target circle and the center of the target is equal to the distance between the center of the second target circle and the center of the target, and the radius of the first target circle is greater than the radius of the second target circle;

[0009] For each wind speed, determining the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the center positions of the first target circle and the second target circle in the target image;

[0010] Determine the inertial force and damping force generated when the target rigid segment model vibrates, and determine the vertical component force corresponding to the relative displacement time history according to the relative displacement time history and the preset conversion relationship between displacement and force;

[0011] Obtain the aerodynamic force of the target rigid segment model based on the vertical component force, the inertial force, and the damping force of the target rigid segment model.

[0012] In a second aspect, the present application provides an aerodynamic force determination device, which includes:

[0013] An acquisition module, configured to acquire the target images of the target rigid segment model at multiple wind speeds after the target rigid segment model reaches a steady state vibration; wherein, the target of the target rigid segment model includes a first target circle, a second target circle, and a cross mark, the cross mark is located at the center of the target, the distance between the center of the first target circle and the center of the target is equal to the distance between the center of the second target circle and the center of the target, and the radius of the first target circle is greater than the radius of the second target circle;

[0014] A displacement time history determination module, configured to, for each wind speed, determine the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the center positions of the first target circle and the second target circle in the target image;

[0015] A component force determination module, configured to determine the inertial force and damping force generated when the target rigid segment model vibrates, and determine the vertical component force corresponding to the relative displacement time history according to the relative displacement time history and the preset conversion relationship between displacement and force;

[0016] An aerodynamic force determination module, configured to obtain the aerodynamic force of the target rigid segment model based on the vertical component force, the inertial force, and the damping force of the target rigid segment model.

[0017] In a third aspect, the present application provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor, where the processor implements the aerodynamic force determination method as described in any embodiment of the present application when executing the program.

[0018] In a fourth aspect, the present application provides a computer-readable storage medium, on which a computer program is stored, and when the program is executed by a processor, it implements the aerodynamic force determination method as described in any embodiment of the present application.

[0019] Fifth aspect, the present application provides a computer program product, including a computer program which, when executed by a processor, implements the aerodynamic force determination method as described in any embodiment of the present application.

[0020] Compared with the prior art, the advantages of the present invention are as follows: after the target rigid segment model reaches a steady state vibration, target images of the target rigid segment model at multiple wind speeds are collected; wherein, the target of the target rigid segment model includes a first target circle, a second target circle and a cross mark, the cross mark is located at the center of the target, the distance between the center of the first target circle and the center of the target is equal to the distance between the center of the second target circle and the center of the target, and the radius of the first target circle is greater than the radius of the second target circle; for each wind speed, according to the center positions of the first target circle and the second target circle in the target image, the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed is determined; the inertial force and damping force generated when the target rigid segment model vibrates are determined, and the vertical component force corresponding to the relative displacement time history is determined according to the relative displacement time history and the preset conversion relationship between displacement and force; the aerodynamic force of the target rigid segment model is obtained according to the vertical component force, the inertial force and the damping force of the target rigid segment model. That is, the solution of the present application determines the relative displacement time history of the target rigid segment model according to the image, and determines the aerodynamic force of the target rigid segment model according to the vertical component force corresponding to the relative displacement time history, thereby avoiding the use of a high-precision dynamometer to measure the aerodynamic force, reducing the experimental cost, reducing the installation difficulty of the experiment, and not requiring repeated measurement of the aerodynamic force by a high-precision dynamometer in repeated wind tunnel tests, thereby improving the experimental efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Hereinafter, the present invention will be described in more detail based on embodiments and with reference to the drawings. Among them:

[0022] Figure 1 is a flowchart of the aerodynamic force determination method provided by the present application;

[0023] Figure 2a is another flowchart of the aerodynamic force determination method provided by the present application;

[0024] Figure 2b is an example diagram of a target rigid segment model of the aerodynamic force determination method provided by the present application;

[0025] Figure 3 is a structural diagram of an aerodynamic force determination device provided by the present application;

[0026] Figure 4 is a structural diagram of an electronic device provided by the present application;

[0027] Reference Signs:

[0028] 1 - Spring; 2 - Model body; 3 - End plate; 4 - Target. Specific implementation mode

[0029] The present invention will be further described in detail below in conjunction with the accompanying drawings of the specification and specific embodiments, but the protection scope of the present invention is not limited thereby.

[0030] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be understood as a limitation to the present invention.

[0031] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, "a plurality" means two or more, unless otherwise specifically defined.

[0032] In the present invention, unless otherwise clearly specified and limited, the terms "assembly", "connected", "connected", "fixed", etc. should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0033] The present invention will be further described in detail below in conjunction with the accompanying drawings of the specification and specific embodiments.

[0034] Figure 1 is a flow schematic diagram of the aerodynamic force determination method provided by the present application. This method can be executed by an aerodynamic force determination device, and this device can be implemented in a software and / or hardware manner. In a specific embodiment, this device can be applied in an electronic device, and the electronic device can be a computer. The following embodiments will be described by taking this device applied in an electronic device as an example. Refer to Figure 1 , and this method can specifically include the following steps:

[0035] Step 101, after the target rigid segment model reaches steady-state vibration, collect the target images of the target rigid segment model at multiple wind speeds.

[0036] Among them, the target of the target rigid segment model includes a first target circle, a second target circle, and a cross mark. The cross mark is located at the center of the target. The distance from the center of the first target circle to the center of the target is equal to the distance from the center of the second target circle to the center of the target, and the radius of the first target circle is greater than the radius of the second target circle.

[0037] Specifically, the target rigid segment model is a model that can simulate the stress conditions of a cable-stayed bridge. One section of the target rigid segment model is pasted with a target for determining the movement of the target rigid segment model in the vertical direction. The target is composed of a large circle and a small circle. The target is pasted on the side of the model, and the center of the cross-section of the model is aligned with the cross mark in the target. The acquisition device for collecting the target images of the target rigid segment model at multiple wind speeds, such as an industrial camera, is installed outside the wind tunnel test chamber and is facing the target position through the transparent glass for easy shooting of the target images. After the target rigid segment model enters steady-state vibration under the influence of any wind speed, the industrial camera collects multiple target images at multiple wind speeds according to the preset camera sampling frequency. Statistical parameter calculations are performed on the data of the multiple target images, and the statistical parameter results are used as the data in the subsequent steps to improve the accuracy of the acquisition results.

[0038] Optionally, the target rigid segment model further includes a spring suspension system, a model body, and more than two end plates; the target is pasted on the model body, and the center of the plane where the width and height of the model body are located coincides with the center of the target; the end plates are respectively nested at both ends of the model body, so that the model body is located between the two end plates; the spring suspension system includes multiple springs, and the lower ends of some of the springs are connected to the upper ends of the end plates, and the upper ends of some of the springs are connected to the lower ends of the end plates, so that the end plates and the model body between the end plates are suspended.

[0039] Specifically, Figure 2b is an example diagram of a target rigid segment model of the aerodynamic force determination method provided by this application. As Figure 2b shown, the spring suspension system includes 8 springs 1, and the lower ends of 4 of the springs 1 are all connected to the upper ends of the end plates 3, and the upper ends of the other 4 springs 1 are all connected to the lower ends of the end plates 3, so that the end plates 3 and the model body 2 between the end plates 3 are suspended. The model body 2 of the rigid segment model is obtained by reducing the cable-stayed bridge according to a preset scale ratio. The number of end plates 3 is two. The target 4 is pasted on the model body 2, and the center of the plane where the width and height of the model body 2 are located coincides with the center of the target 4. The two end plates 3 are respectively nested at both ends of the model body 2, so that the model body 2 is located between the two end plates 3.

[0040] Step 102: For each wind speed, determine the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the center positions of the first target circle and the second target circle in the target image.

[0041] Among them, the target wind speed is a value set according to actual requirements. For example, the target wind speed can be 0.

[0042] Specifically, the displacement time history refers to the displacement change of an object within a preset time. Usually, time is used as the abscissa and displacement as the ordinate to draw a curve. The relative displacement time history in this embodiment is the relative difference that can characterize the displacement change of the target rigid segment model at the current wind speed and its displacement change at the target wind speed. For example, subtract the displacement time history curve of the target rigid segment model at the current wind speed from the displacement time history curve of the target rigid segment model at the target wind speed within the same time, and the obtained curve is the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed. Determine the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the moving conditions of the center positions of the first target circle and the second target circle in the experiment relative to the wind speed of 0, that is, the displacement time history caused by the vertical component force during model vibration.

[0043] Optionally, before determining the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the center positions of the first target circle and the second target circle in the target image, steps 21 to 22 can also be executed.

[0044] Step 21: Determine the diameters of the first target circle and the second target circle according to the target image.

[0045] Specifically, use an edge detection algorithm to process the pictures collected at different wind speeds, and obtain the diameters of the first target circle and the second target circle through the edge detection results of the first target circle and the second target circle.

[0046] Step 22: Determine the center positions of the first target circle and the second target circle according to the diameters of the first target circle and the second target circle.

[0047] Specifically, use an edge detection algorithm to process the pictures collected at different wind speeds, and obtain the center positions of the first target circle and the second target circle through the edge detection results of the first target circle and the second target circle.

[0048] Optionally, after performing steps 21 to 22, determining the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed based on the center positions of the first target circle and the second target circle in the target image can be achieved through steps 1021 to 1022.

[0049] Step 1021: Determine the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the pixel coordinates of the center of the first target circle, and the pixel coordinates of the center of the second target circle based on the diameter of the first target circle, the diameter of the second target circle, the center position of the first target circle, and the center position of the second target circle.

[0050] Step 1022: Determine the relative displacement time history of the wind speed relative to the target wind speed based on the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the pixel coordinates of the center of the first target circle, and the pixel coordinates of the center of the second target circle.

[0051] Specifically, convert the pixel coordinates into physical coordinates through a preset proportional relationship to obtain the relative displacement time history of the model at each wind speed relative to the model at 0 wind speed.

[0052] Optionally, step 1022 can be achieved through steps 221 to 222.

[0053] Step 221: Obtain the physical coordinates of the diameter of the first target circle, the physical coordinates of the diameter of the second target circle, the physical coordinates of the center of the first target circle, and the physical coordinates of the center of the second target circle based on the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the pixel coordinates of the center of the first target circle, the pixel coordinates of the center of the second target circle, and the preset conversion ratio between pixel coordinates and physical coordinates.

[0054] Step 222: Determine the relative displacement time history of the wind speed relative to the target wind speed based on the physical coordinates of the diameter of the first target circle, the physical coordinates of the diameter of the second target circle, the physical coordinates of the center of the first target circle, and the physical coordinates of the center of the second target circle.

[0055] Exemplarily, edge detection processes each picture to obtain the edge pixel points of the first target circle and the second target circle, takes the maximum distance between the edge pixel points in the respective regions of the first target circle and the second target circle as the diameter, and takes the center of the two points with the maximum distance as the center of the circle. The preset conversion ratio relationship between pixel coordinates and physical coordinates is: the relative vertical displacements (in pixels) of the model at each wind speed compared to the model at 0 wind speed are respectively . The relative vertical displacement in physical coordinates can be expressed as follows, and the change in relative vertical displacement over a period of time is the relative vertical displacement time history.

[0056]

[0057] Wherein, is the physical size of each pixel. For example, the physical size of a pixel can be 0.1 mm.

[0058] Step 103: Determine the inertial force and damping force of the target rigid segment model, and determine the vertical component force corresponding to the relative displacement time history according to the relative displacement time history and the preset conversion relationship between displacement and force.

[0059] Specifically, the inertial force of the target rigid segment model is the inertial force caused by the total mass during the vibration of the model body and part of the springs. For example, the spring mass is included in 1 / 3 of the total spring mass. The damping force is the model damping force obtained according to the velocity of the model during vibration and the damping ratio of the model. The inertial force and damping force of the model can be determined by Formula 1.

[0060] Formula 1

[0061] Wherein, represents the inertial force, represents the damping force, is the total mass of the model body and the springs during vibration, and the spring mass is included in 1 / 3 of the total spring mass. , are the acceleration and velocity of the model during vibration, respectively. is the damping coefficient of the model during vibration. The damping coefficient can be obtained from Formula 2.

[0062] Formula 2

[0063] Wherein, is the damping ratio of the model, and the damping ratio of the model is approximately obtained by the free vibration and logarithmic decrement method of the model, is the overall stiffness of the model.

[0064] The preset conversion relationship between displacement and force is a preset relationship between the longitudinal displacement of the model and the vertical force received by the model. The determination process of the preset conversion relationship between displacement and force is as follows: In the upper part of the example diagram of the target rigid segment model shown in Figure 2b , after the model undergoes displacement, the lateral displacement, vertical displacement, and angular displacement are respectively , , . When the model undergoes displacement, both sides of the model are regarded as undergoing displacement simultaneously as a whole, so only the displacement of one side needs to be considered. For the 4 springs used for single-side suspension, let be the original length of the spring, is the stiffness of a spring, and and and are the total lengths of the springs after static stretching at the upper ends of the left suspension, upper ends of the right suspension, lower ends of the left suspension, and lower ends of the right suspension, respectively. and and and are the total suspension lengths at the upper ends of the left suspension, upper ends of the right suspension, lower ends of the left suspension, and lower ends of the right suspension, respectively. and and and are the deformation amounts of the springs after static stretching at the upper ends of the left suspension, upper ends of the right suspension, lower ends of the left suspension, and lower ends of the right suspension, respectively. and and and are the total suspension lengths without the spring deformation amounts at the upper ends of the left suspension, upper ends of the right suspension, lower ends of the left suspension, and lower ends of the right suspension, respectively. and and and and and and and As shown in Equation 3,

[0065] Equation 3

[0066] In the upper half of the example diagram of the target rigid segment model as shown in Figure 2b , that is, for the 4 springs used on one side of the suspension, and and and are the lateral displacements that occur in the plane at the four suspension points on one side, respectively, and and and are the vertical displacements that occur in the plane at the four suspension points on one side, respectively. and and and and and and and can be expressed by Equations 4 to 7.

[0067] Equation 4

[0068] Equation 5

[0069] Formula 6

[0070] Formula 7

[0071] Wherein, represents the distance between the left and right suspensions, represents the distance between the upper and lower suspensions.

[0072] The process of obtaining the displacement - force conversion relationship of the springs at the four suspension points on one side is shown in Formulas 8 to 12.

[0073] Formula 8

[0074] Formula 9

[0075] Formula 10

[0076] Formula 11

[0077] Formula 12

[0078] Wherein, , , , are respectively the forces of the springs on one - side four - sides after displacement, , , , are respectively the angles with the vertical direction of the springs on one - side four - sides after displacement. , , , are respectively the vertical change component forces of the springs on one - side four - sides after displacement. , , , are respectively the torques of the springs on one - side four - sides on the center point of the model after displacement. , , are respectively the vertical component force, horizontal component force and torque corresponding to the displacement after the model is displaced. Thus, the vertical component force corresponding to the relative displacement time - history can be determined according to the relative displacement time - history and the preset displacement - force conversion relationship.

[0079] Step 104, obtain the aerodynamic force of the target rigid segment model according to the vertical component force, the inertial force and the damping force of the target rigid segment model.

[0080] Specifically, after obtaining the vertical component force, the inertial force, and the damping force of the target rigid segment model, the aerodynamic force can be obtained by subtracting the inertial force and the damping force from the vertical component force. That is, the aerodynamic force can be determined by Equation 13.

[0081] Equation 13

[0082] Wherein, represents the aerodynamic force, represents the vertical component force, represents the inertial force, represents the damping force.

[0083] In the solution of the present application, after the target rigid segment model reaches steady-state vibration, target images of the target rigid segment model at multiple wind speeds are collected; wherein, the targets of the target rigid segment model include a first target circle, a second target circle, and a cross mark, the cross mark is located at the center of the target, the distance between the center of the first target circle and the center of the target is equal to the distance between the center of the second target circle and the center of the target, and the radius of the first target circle is greater than the radius of the second target circle; for each wind speed, according to the center positions of the first target circle and the second target circle in the target image, the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed is determined; the inertial force and the damping force generated when the target rigid segment model vibrates are determined, and the vertical component force corresponding to the relative displacement time history is determined according to the relative displacement time history and the preset conversion relationship between displacement and force; the aerodynamic force of the target rigid segment model is obtained according to the vertical component force, the inertial force, and the damping force of the target rigid segment model. That is, in the solution of the present application, the relative displacement time history of the target rigid segment model is determined according to the image, and the aerodynamic force of the target rigid segment model is determined according to the vertical component force corresponding to the relative displacement time history, thereby avoiding the use of a high-precision dynamometer to measure the aerodynamic force, reducing the experimental cost, and reducing the installation difficulty of the experiment. There is no need to repeatedly measure the aerodynamic force through a high-precision dynamometer in repeated wind tunnel tests, thereby improving the experimental efficiency.

[0084] Figure 2a is another flow schematic diagram of the aerodynamic force determination method provided by the present application. In this embodiment, Figure 1 on the basis of the embodiments and various optional implementation schemes shown, the steps of obtaining the inertial force and the damping force generated when the target rigid segment model vibrates are described in detail. As Figure 2a shown, the method may include the following steps:

[0085] Step 201, after the target rigid segment model reaches steady-state vibration, collect target images of the target rigid segment model at multiple wind speeds.

[0086] Step 202: For each wind speed, determine the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the center positions of the first target circle and the second target circle in the target image.

[0087] Step 203: Obtain the total mass and acceleration of the target rigid segment model during vibration.

[0088] Exemplarily, the total mass of the target rigid segment model during vibration is m, and the acceleration a is determined according to the time corresponding to the longitudinal displacement and the longitudinal displacement of the target rigid segment model during vibration.

[0089] Step 204: Determine the inertial force generated by the target rigid segment model during vibration according to the total mass and the acceleration.

[0090] Specifically, the total mass of the target rigid segment model during vibration is m, and the acceleration is a, so the inertial force can be obtained as is = ma.

[0091] Step 205: Obtain the velocity of the target rigid segment model during vibration and the damping coefficient of the target rigid segment model.

[0092] Exemplarily, the velocity v is determined according to the time corresponding to the longitudinal displacement and the longitudinal displacement of the target rigid segment model during vibration. The damping coefficient of the target rigid segment model can be obtained according to the damping ratio and the mass, and the damping ratio of the target rigid segment model can be approximately obtained according to the free vibration of the model and the logarithmic decrement method.

[0093] Step 206: Determine the damping force generated by the target rigid segment model during vibration according to the velocity of the target rigid segment model during vibration and the damping coefficient.

[0094] Specifically, the damping ratio of the target rigid segment model is c, and the velocity during vibration is v, so the damping force can be obtained as is = cv.

[0095] Step 207: Determine the vertical component force corresponding to the relative displacement time history according to the relative displacement time history and the preset conversion relationship between displacement and force.

[0096] Step 208: Obtain the aerodynamic force of the target rigid segment model according to the vertical component force, the inertial force and the damping force of the target rigid segment model.

[0097] The solution of the present application can accurately calculate the inertial force and the damping force to more accurately determine the aerodynamic force, thereby improving the reliability, safety and anti-interference ability of the experiment, optimizing the determination effect of the aerodynamic force, and having simple calculation and improved experimental efficiency.

[0098] Figure 3 is a structural schematic diagram of the aerodynamic force determination device provided by this application, and this device is applicable to execute the aerodynamic force determination method provided by this application. As Figure 3 shown, this device may specifically include:

[0099] An acquisition module 301, configured to acquire target images of the target rigid segment model at multiple wind speeds after the target rigid segment model reaches steady-state vibration; wherein, the targets of the target rigid segment model include a first target circle, a second target circle, and a cross mark, the cross mark is located at the center of the target, the distance between the center of the first target circle and the center of the target is equal to the distance between the center of the second target circle and the center of the target, and the radius of the first target circle is greater than the radius of the second target circle.

[0100] A displacement time history determination module 302, configured to, for each wind speed, determine the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the center positions of the first target circle and the second target circle in the target image.

[0101] A component force determination module 303, configured to determine the inertial force and damping force generated when the target rigid segment model vibrates, and determine the vertical component force corresponding to the relative displacement time history according to the relative displacement time history and a preset conversion relationship between displacement and force.

[0102] An aerodynamic force determination module 304, configured to obtain the aerodynamic force of the target rigid segment model according to the vertical component force, the inertial force, and the damping force of the target rigid segment model.

[0103] In one embodiment, the device further includes: a center determination module, configured to, before the displacement time history determination module 302 determines the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the center positions of the first target circle and the second target circle in the target image, determine the diameters of the first target circle and the second target circle according to the target image; and determine the center positions of the first target circle and the second target circle according to the diameters of the first target circle and the second target circle.

[0104] In one embodiment, the displacement time history determination module 302 is specifically configured to: determine the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the pixel coordinates of the center of the first target circle, and the pixel coordinates of the center of the second target circle according to the diameter of the first target circle, the diameter of the second target circle, the center position of the first target circle, and the center position of the second target circle; determine the relative displacement time history of the wind speed relative to the target wind speed according to the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the pixel coordinates of the center of the first target circle, and the pixel coordinates of the center of the second target circle.

[0105] In one embodiment, when the displacement time history determination module 302 determines the relative displacement time history of the wind speed relative to the target wind speed according to the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the pixel coordinates of the center of the first target circle, and the pixel coordinates of the center of the second target circle, it is specifically configured to: obtain the physical coordinates of the diameter of the first target circle, the physical coordinates of the diameter of the second target circle, the physical coordinates of the center of the first target circle, and the physical coordinates of the center of the second target circle according to the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the pixel coordinates of the center of the first target circle, the pixel coordinates of the center of the second target circle, and a preset conversion ratio between pixel coordinates and physical coordinates; determine the relative displacement time history of the wind speed relative to the target wind speed according to the physical coordinates of the diameter of the first target circle, the physical coordinates of the diameter of the second target circle, the physical coordinates of the center of the first target circle, and the physical coordinates of the center of the second target circle.

[0106] In one embodiment, when the component force determination module 303 determines the inertial force generated during the vibration of the target rigid segment model, it is specifically configured to: obtain the total mass and acceleration during the vibration of the target rigid segment model; determine the inertial force generated during the vibration of the target rigid segment model according to the total mass and the acceleration.

[0107] In one embodiment, when the component force determination module 303 determines the damping force generated during the vibration of the target rigid segment model, it is specifically configured to: obtain the velocity during the vibration of the target rigid segment model and the damping coefficient of the target rigid segment model; determine the damping force generated during the vibration of the target rigid segment model according to the velocity during the vibration of the target rigid segment model and the damping coefficient.

[0108] In one embodiment, the target rigid segment model further includes a spring suspension system, a model body, and more than two end plates; the target is attached to the model body, and the center of the surface where the width and height of the model body are located coincides with the center of the target; the end plates are respectively nested at both ends of the model body, so that the model body is located between the two end plates; the spring suspension system includes a plurality of springs, wherein the lower ends of some of the springs are connected to the upper ends of the end plates, and the upper ends of some of the springs are connected to the lower ends of the end plates, so that the end plates and the model body between the end plates are suspended.

[0109] For the device of the present application, after the target rigid segment model reaches a steady state vibration, target images of the target rigid segment model at multiple wind speeds are collected; wherein, the target of the target rigid segment model includes a first target circle, a second target circle, and a cross mark, the cross mark is located at the center of the target, the distance from the center of the first target circle to the center of the target is equal to the distance from the center of the second target circle to the center of the target, and the radius of the first target circle is greater than the radius of the second target circle; for each wind speed, according to the center positions of the first target circle and the second target circle in the target image, the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed is determined; the inertial force and damping force generated when the target rigid segment model vibrates are determined, and the vertical component force corresponding to the relative displacement time history is determined according to the relative displacement time history and the preset conversion relationship between displacement and force; the aerodynamic force of the target rigid segment model is obtained according to the vertical component force, the inertial force, and the damping force of the target rigid segment model. That is, in the solution of the present application, the relative displacement time history of the target rigid segment model is determined according to the image, and the aerodynamic force of the target rigid segment model is determined according to the vertical component force corresponding to the relative displacement time history, thereby avoiding the use of a high-precision dynamometer to measure the aerodynamic force, reducing the experimental cost, and reducing the installation difficulty of the experiment. There is no need to repeatedly measure the aerodynamic force with a high-precision dynamometer in repeated wind tunnel tests, thereby improving the experimental efficiency.

[0110] The present application also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, the aerodynamic force determination method provided in any of the above embodiments is implemented.

[0111] The present application also provides a computer-readable medium, on which a computer program is stored. When the program is executed by a processor, the aerodynamic force determination method provided in any of the above embodiments is implemented.

[0112] Reference is made below to Figure 4 , which shows a schematic structural diagram of an electronic device 400 suitable for implementing the present application. Figure 4 The electronic device shown is only an example and should not impose any limitation on the functions and usage scope of the present application.

[0113] As shown Figure 4 in FIG. 400, the electronic device 400 includes a central processing unit (CPU) 401 that can perform various appropriate actions and processes according to a program stored in a read-only memory (ROM) 402 or a program loaded from a storage section 408 into a random access memory (RAM) 403. In the RAM 403, various programs and data required for the operation of the electronic device 400 are also stored. The CPU 401, ROM 402, and RAM 403 are connected to each other via a bus 404. An input / output (I / O) interface 405 is also connected to the bus 404.

[0114] The following components are connected to the I / O interface 405: an input section 406 including a keyboard, a mouse, etc.; an output section 407 including a cathode ray tube (CRT), a liquid crystal display (LCD), etc. and a speaker, etc.; a storage section 408 including a hard disk, etc.; and a communication section 409 including a network interface card such as a LAN card, a modem, etc. The communication section 409 performs communication processing via a network such as the Internet. A drive 410 is also connected to the I / O interface 405 as required. A removable medium 411, such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, etc., is mounted on the drive 410 as required so that a computer program read from it can be installed into the storage section 408 as required.

[0115] Specifically, according to the embodiments disclosed in the present application, the processes described above with reference to the flowcharts can be implemented as computer software programs. For example, the embodiments disclosed in the present application include a computer program product that includes a computer program carried on a computer-readable medium, and the computer program includes program codes for performing the methods shown in the flowcharts. In such an embodiment, the computer program can be downloaded and installed from a network via the communication section 409, and / or installed from the removable medium 411. When the computer program is executed by the central processing unit (CPU) 401, the above functions defined in the system of the present application are executed.

[0116] It should be noted that the computer-readable medium shown in this application can be a computer-readable signal medium, a computer-readable storage medium, or any combination of the two. A computer-readable storage medium can be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the above. More specific examples of a computer-readable storage medium can include, but are not limited to: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above. In this application, a computer-readable storage medium can be any tangible medium that contains or stores a program, and this program can be used by or in conjunction with an instruction execution system, apparatus, or device. In this application, a computer-readable signal medium can include a data signal propagated in a baseband or as part of a carrier wave, which carries computer-readable program code. Such a propagated data signal can take various forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. A computer-readable signal medium can also be any computer-readable medium other than a computer-readable storage medium, and this computer-readable medium can send, propagate, or transmit a program for use by or in conjunction with an instruction execution system, apparatus, or device. The program code contained on a computer-readable medium can be transmitted using any appropriate medium, including but not limited to: wireless, wire, optical cable, RF, etc., or any suitable combination of the above.

[0117] The flowcharts and block diagrams in the accompanying drawings illustrate the possible architectures, functions, and operations of systems, methods, and computer program products according to various embodiments of this application. In this regard, each block in a flowchart or block diagram can represent a module, a program segment, or a part of code, and the above module, program segment, or part of code contains one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions marked in the blocks can occur in a different order than that marked in the accompanying drawings. For example, two consecutive blocks shown can actually be executed substantially in parallel, and they can sometimes be executed in the reverse order, depending on the functions involved. It should also be noted that each block in a block diagram or flowchart, and the combination of blocks in a block diagram or flowchart, can be implemented by a dedicated hardware-based system for performing the specified functions or operations, or can be implemented by a combination of dedicated hardware and computer instructions.

[0118] The modules and / or units involved in this application can be implemented in software or in hardware. The described modules and / or units can also be provided in a processor. For example, it can be described as: A processor includes an acquisition module, a displacement time history determination module, a component force determination module, and an aerodynamic force determination module. Among them, the names of these modules do not constitute a limitation to the modules themselves in some cases.

[0119] As another aspect, this application also provides a computer-readable medium. The computer-readable medium can be included in the device described in the above embodiments; or it can exist independently without being assembled into the device. The above computer-readable medium carries one or more programs. When the above one or more programs are executed by the device, the device is caused to perform the following operations:

[0120] After the steady-state vibration of the target rigid segment model, acquire the target images of the target rigid segment model at multiple wind speeds; wherein, the targets of the target rigid segment model include a first target circle, a second target circle, and a cross mark. The cross mark is located at the center of the target. The distance between the center of the first target circle and the center of the target is equal to the distance between the center of the second target circle and the center of the target, and the radius of the first target circle is greater than the radius of the second target circle; for each wind speed, determine the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the center positions of the first target circle and the second target circle in the target image; determine the inertial force and damping force generated when the target rigid segment model vibrates, and determine the vertical component force corresponding to the relative displacement time history according to the relative displacement time history and the preset conversion relationship between displacement and force; obtain the aerodynamic force of the target rigid segment model according to the vertical component force, the inertial force, and the damping force of the target rigid segment model.

[0121] According to the technical solution of the present application, after the steady-state vibration of the target rigid segment model, target images of the target rigid segment model at multiple wind speeds are collected; wherein, the targets of the target rigid segment model include a first target circle, a second target circle, and a cross mark, the cross mark is located at the center of the target, the distance between the center of the first target circle and the center of the target is equal to the distance between the center of the second target circle and the center of the target, and the radius of the first target circle is greater than the radius of the second target circle; for each wind speed, according to the center positions of the first target circle and the second target circle in the target image, the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed is determined; the inertial force and damping force generated when the target rigid segment model vibrates are determined, and the vertical component force corresponding to the relative displacement time history is determined according to the relative displacement time history and the preset conversion relationship between displacement and force; the aerodynamic force of the target rigid segment model is obtained according to the vertical component force, the inertial force, and the damping force of the target rigid segment model. That is, the solution of the present application determines the relative displacement time history of the target rigid segment model according to the image, and determines the aerodynamic force of the target rigid segment model according to the vertical component force corresponding to the relative displacement time history, thereby avoiding the use of a high-precision dynamometer to measure the aerodynamic force, reducing the experimental cost, and reducing the installation difficulty of the experiment. There is no need to repeatedly measure the aerodynamic force with a high-precision dynamometer in repeated wind tunnel tests, thereby improving the experimental efficiency.

[0122] The embodiment of the present application further provides a computer program product, including a computer program, which implements the aerodynamic force determination method provided in any embodiment of the present application when executed by a processor.

[0123] In the process of implementing the computer program product, the computer program code for executing the operations of the present application can be written in one or more programming languages or combinations thereof. The programming languages include object-oriented programming languages such as Java, Smalltalk, C++, and also include conventional procedural programming languages such as the "C" language or similar programming languages. The program code can be executed entirely on the user's computer, partially on the user's computer, executed as an independent software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In the case of a remote computer, the remote computer can be connected to the user's computer through any type of network - including a local area network (LAN) or a wide area network (WAN) - or can be connected to an external computer (for example, by using an Internet service provider to connect through the Internet).

[0124] It should be understood that the various forms of processes shown above can be used, with steps reordered, added, or deleted. For example, the steps described in this application can be executed in parallel, sequentially, or in a different order, as long as the desired results of the technical solution of this application can be achieved, and no limitation is imposed herein.

[0125] Although the present invention has been described with reference to preferred embodiments, various modifications can be made to it and components therein can be replaced with equivalents without departing from the scope of the present invention. In particular, as long as there is no structural conflict, the various technical features mentioned in each embodiment can be combined in any manner. The present invention is not limited to the specific embodiments disclosed in the text, but includes all technical solutions falling within the scope of the claims.

Claims

1. An aerodynamic force determination method, characterized in that, The method includes: After the target rigid segment model reaches steady-state vibration, acquiring target images of the target rigid segment model at multiple wind speeds; wherein, the target of the target rigid segment model includes a first target circle, a second target circle, and a cross mark, the cross mark is located at the center of the target, the distance between the center of the first target circle and the center of the target is equal to the distance between the center of the second target circle and the center of the target, and the radius of the first target circle is greater than the radius of the second target circle; For each wind speed, determining the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the pixel coordinates of the center of the first target circle, and the pixel coordinates of the center of the second target circle according to the diameter of the first target circle, the diameter of the second target circle, the center position of the first target circle, and the center position of the second target circle; According to the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the pixel coordinates of the center of the first target circle, the pixel coordinates of the center of the second target circle, and a preset conversion ratio between pixel coordinates and physical coordinates, obtaining the physical coordinates of the diameter of the first target circle, the physical coordinates of the diameter of the second target circle, the physical coordinates of the center of the first target circle, and the physical coordinates of the center of the second target circle; According to the physical coordinates of the diameter of the first target circle, the physical coordinates of the diameter of the second target circle, the physical coordinates of the center of the first target circle, and the physical coordinates of the center of the second target circle, determining the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed; Determining the inertial force and damping force generated when the target rigid segment model vibrates, and determining the vertical component force corresponding to the relative displacement time history according to the relative displacement time history and a preset conversion relationship between displacement and force; Obtaining the aerodynamic force of the target rigid segment model according to the vertical component force, the inertial force, and the damping force of the target rigid segment model; Before determining the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the center position of the first target circle and the center position of the second target circle in the target image, the method further includes: Determining the diameter of the first target circle and the diameter of the second target circle according to the target image; Determining the center position of the first target circle and the center position of the second target circle according to the diameter of the first target circle and the diameter of the second target circle.

2. The method according to claim 1, characterized in that, The determining of the inertial force generated when the target rigid segment model vibrates includes: Obtaining the total mass and acceleration when the target rigid segment model vibrates; Determining the inertial force generated when the target rigid segment model vibrates according to the total mass and the acceleration.

3. The method according to claim 1, wherein Determining the damping force generated when the target rigid segment model vibrates includes: Obtaining the velocity when the target rigid segment model vibrates and the damping coefficient of the target rigid segment model; Determine the damping force generated during the vibration of the target rigid segment model based on the velocity during the vibration of the target rigid segment model and the damping coefficient.

4. The method according to claim 1, wherein The target rigid segment model further includes a spring suspension system, a model body, and more than two end plates; The target is attached to the model body, and the center of the surface where the width and height of the model body are located coincides with the center of the target; The end plates are respectively nested at both ends of the model body, such that the model body is located between the two end plates; The spring suspension system includes multiple springs, wherein the lower ends of some of the springs are connected to the upper ends of the end plates, and the upper ends of some of the springs are connected to the lower ends of the end plates, so as to suspend the end plates and the model body between the end plates.

5. An aerodynamic force determination device, characterized in that, The device includes: An acquisition module, configured to acquire target images of the target rigid segment model at multiple wind speeds after the target rigid segment model reaches steady-state vibration; wherein, the target of the target rigid segment model includes a first target circle, a second target circle, and a cross mark, the cross mark is located at the center of the target, the distance between the center of the first target circle and the center of the target is equal to the distance between the center of the second target circle and the center of the target, and the radius of the first target circle is greater than the radius of the second target circle; A displacement time history determination module, configured to determine the diameter of the first target circle and the diameter of the second target circle according to the target images; determine the center position of the first target circle and the center position of the second target circle according to the diameter of the first target circle and the diameter of the second target circle; for each wind speed, determine the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the pixel coordinates of the center of the first target circle, and the pixel coordinates of the center of the second target circle according to the diameter of the first target circle, the diameter of the second target circle, the center position of the first target circle, and the center position of the second target circle; obtain the physical coordinates of the diameter of the first target circle, the physical coordinates of the diameter of the second target circle, the physical coordinates of the center of the first target circle, and the physical coordinates of the center of the second target circle according to the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the pixel coordinates of the center of the first target circle, the pixel coordinates of the center of the second target circle, and a preset conversion ratio between pixel coordinates and physical coordinates; determine the relative displacement time history between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed according to the physical coordinates of the diameter of the first target circle, the physical coordinates of the diameter of the second target circle, the physical coordinates of the center of the first target circle, and the physical coordinates of the center of the second target circle; A component force determination module, configured to determine the inertial force and the damping force generated during the vibration of the target rigid segment model, and determine the vertical component force corresponding to the relative displacement time history according to the relative displacement time history and a preset conversion relationship between displacement and force; An aerodynamic force determination module, configured to obtain the aerodynamic force of the target rigid segment model according to the vertical component force, the inertial force of the target rigid segment model, and the damping force.

6. An electronic device, comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, When the processor executes the program, the aerodynamic force determination method according to any one of claims 1 to 4 is implemented.

7. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the program is executed by the processor, the aerodynamic force determination method according to any one of claims 1 to 4 is implemented.

Images