Aerodynamic force determination method and device, electronic equipment and storage medium

Abstract

The invention provides an aerodynamic force determination method and device, electronic equipment and a storage medium, and relates to the technical field of cable-stayed bridges, and the method comprises the steps: collecting target images of a target rigid segment model at a plurality of wind speeds after the steady-state vibration of the target rigid segment model; for each wind speed, according to the circle center position of a first target circle and the circle center position of a second target circle in the target image, determining a 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 a vertical component force corresponding to the relative displacement time history according to the relative displacement time history and a conversion relation between preset displacement and force; and obtaining the aerodynamic force of the target rigid segment model according to the vertical component force, the inertia force of the target rigid segment model and the damping force. According to the scheme provided by the invention, a high-precision dynamometer is prevented from being used for measuring the aerodynamic force, so that the experiment cost is reduced, the installation difficulty of the experiment is reduced, and the experiment efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of cable-stayed bridges, and in particular to an aerodynamic force determination method, device, electronic equipment and storage medium. Background Art

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

[0003] At present, the research method of cable vortex-induced resonance is to obtain the aerodynamic force of the cable rigid model using high-precision force sensors in wind tunnel tests.

[0004] However, in wind tunnel tests, high-precision force sensors are not only expensive, but also complicated to install during 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 shortcomings of the prior art and provide an aerodynamic force determination method, device, electronic device and storage medium to solve the problem in the prior art that in wind tunnel tests, high-precision force sensors are not only expensive, but also complicated to install during experiments and have low experimental efficiency.

[0006] In order to solve the above technical problems, the technical solution proposed by the present invention is: In a first aspect, the present application provides a method for determining an aerodynamic force, the method comprising: After the target rigid segment model vibrates in a steady state, 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, determining a relative displacement time history between a target rigid segment model at a current wind speed and a target rigid segment model at a target wind speed according to a center position of the first target circle and a center position of 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 a conversion relationship between a preset displacement and force; The aerodynamic force of the target rigid segment model is obtained according to the vertical component force, the inertial force of the target rigid segment model and the damping force.

[0007] In a second aspect, the present application provides an aerodynamic force determination device, the device comprising: An acquisition module is used to acquire target images of the target rigid segment model at multiple wind speeds after the target rigid segment model vibrates in a steady state; 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, for determining, for each wind speed, a relative displacement time history between a target rigid segment model at a current wind speed and a target rigid segment model at a target wind speed according to a center position of the first target circle and a center position of the second target circle in the target image; A component force determination module, used 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 series according to the relative displacement time series and a conversion relationship between a preset displacement and force; The aerodynamic force determination module is used 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.

[0008] In a third aspect, the present application provides an electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, the aerodynamic force determination method as described in any embodiment of the present application is implemented.

[0009] In a fourth aspect, the present application provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the aerodynamic force determination method as described in any embodiment of the present application.

[0010] In a 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.

[0011] Compared with the prior art, the advantages of the present invention are: after the target rigid segment model vibrates in a steady state, target images of the target rigid segment model under 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, 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 according to the center position of the first target circle and the center position of the second target circle in the target image; 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 conversion relationship between the preset 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 series of the target rigid segment model based on the image, and determines the aerodynamic force of the target rigid segment model based on the vertical component force corresponding to the relative displacement time series, thereby avoiding the use of high-precision dynamometers to measure the aerodynamic force, thereby reducing the experimental cost and the difficulty of experimental installation. There is no need to repeatedly measure the aerodynamic force with high-precision dynamometers in repeated wind tunnel tests, thereby improving the experimental efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] The present invention will be described in more detail below based on embodiments and with reference to the accompanying drawings, wherein: Figure 1 is a flow chart of the aerodynamic force determination method provided by the present application; Figure 2a is another flow chart of the method for determining aerodynamic force provided by the present application; Figure 2b is an example diagram of a target rigid segment model of the aerodynamic force determination method provided in the present application; Figure 3 is a structural schematic diagram of the aerodynamic force determination device provided by the present application; Figure 4 is a structural schematic diagram of an electronic device provided by the present application; Reference numerals: 1-spring; 2-model body; 3-end plate; 4-target. DETAILED DESCRIPTION

[0013] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments, but the protection scope of the present invention is not limited thereby.

[0014] In the description of the present invention, it should be understood that the terms "length", "width", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside" and "outside" etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are 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 therefore should not be understood as a limitation on the present invention.

[0015] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0016] In the present invention, unless otherwise clearly specified and limited, the terms "assemble", "connect", "connect", "fix" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0017] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0018] Figure 1 The present invention provides a flow chart of the method for determining aerodynamic force, which can be performed by an aerodynamic force determination device, which can be implemented in software and / or hardware. In a specific embodiment, the device can be applied to an electronic device, which can be a computer. The following embodiments will be described by taking the application of the device in an electronic device as an example, with reference to Figure 1 , the method may specifically include the following steps: Step 101 : After the target rigid segment model vibrates in a steady state, target images of the target rigid segment model under multiple wind speeds are collected.

[0019] 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 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.

[0020] Specifically, the target rigid segment model is a model that can simulate the stress conditions of a cable-stayed bridge. A target is attached to a section of the target rigid segment model to determine 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 attached to 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 equipment for collecting target images of the target rigid segment model at multiple wind speeds, such as an industrial camera, is set up outside the wind tunnel test chamber, facing the target position through transparent glass to facilitate the capture of 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 a preset camera sampling frequency. Statistical parameter calculation is performed on the data of multiple target images, and the statistical parameter results are used as data in subsequent steps to improve the accuracy of the acquisition results.

[0021] Optionally, the target rigid segment model also 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 multiple springs, wherein the lower ends of some springs are connected to the upper ends of the end plates, and the upper ends of some 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.

[0022] Specifically, Figure 2b is an example diagram of a target rigid segment model of the aerodynamic force determination method provided in this application. Figure 2b As shown, the spring suspension system includes 8 springs 1, wherein the lower ends of 4 springs 1 are connected to the upper ends of the end plates 3, and the upper ends of the other 4 springs 1 are 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. There are two end plates 3. The target 4 is attached to the model body 2, and the center of the surface 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 the two ends of the model body 2, so that the model body 2 is located between the two end plates 3.

[0023] Step 102, for each 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, 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.

[0024] The target wind speed is a value set according to actual needs. For example, the target wind speed may be 0.

[0025] Specifically, the displacement time history refers to the displacement change of an object within a preset time, and a curve is usually drawn with time as the horizontal coordinate and displacement as the vertical coordinate. The relative displacement time history in this embodiment is the relative difference between the displacement change of the target rigid segment model at the current wind speed and the displacement change of the target rigid segment model at the target wind speed. For example, the displacement time history curve of the target rigid segment model at the current wind speed is subtracted from the displacement time history curve of the target rigid segment model at the target wind speed in the same time, and the resulting 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. According to the movement of the center position of the first target circle and the center position of the second target circle relative to the wind speed 0 in the experiment, 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, that is, the displacement time history caused by the vertical component force when the model vibrates.

[0026] Optionally, steps 21 to 22 may be performed 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.

[0027] Step 21, determining the diameter of the first target circle and the diameter of the second target circle according to the target image.

[0028] Specifically, an edge detection algorithm is used to process images collected at different wind speeds, and the diameter of the first target circle and the diameter of the second target circle are obtained through edge detection results of the first target circle and the second target circle.

[0029] Step 22, 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.

[0030] Specifically, an edge detection algorithm is used to process images collected at different wind speeds, and the center position of the first target circle and the center position of the second target circle are obtained through edge detection results of the first target circle and the second target circle.

[0031] Optionally, after executing steps 21 to 22, determining the relative displacement time series between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed can be achieved through steps 1021 to 1022 based on the center position of the first target circle and the center position of the second target circle in the target image.

[0032] Step 1021, 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, 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.

[0033] Step 1022, determining the relative displacement time course of the wind speed with respect 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.

[0034] Specifically, the pixel coordinates are converted 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 zero wind speed.

[0035] Optionally, step 1022 may be implemented through steps 221 to 222 .

[0036] Step 221, 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 conversion ratio of the preset pixel coordinates to the physical coordinates, 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.

[0037] Step 222, determining the relative displacement time course 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.

[0038] For example, edge detection processes each image to obtain edge pixel points of the first target circle and the second target circle, and takes the maximum distance between the edge pixel points of the first target circle and the second target circle as the diameter, and the center of the two points with the maximum distance as the center of the circle. The preset conversion ratio between pixel coordinates and physical coordinates is: the relative vertical displacement (in pixels) of each wind speed model compared to the 0 wind speed model is respectively The relative vertical displacement of its physical coordinates It can be expressed as the following formula: the change of relative vertical displacement over a period of time is the relative vertical displacement time history.

[0039] in, The physical size of each pixel. For example, the physical size of a pixel may be 0.1 mm.

[0040] Step 103, determining the inertial force and damping force of the target rigid segment model, 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.

[0041] Specifically, the inertia force of the target rigid segment model is the inertia force caused by the total mass of the model body and part of the spring when vibrating. 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 speed of the model when vibrating and the damping ratio of the model. The inertia force and damping force of the model can be determined by formula 1.

[0042] Formula 1 in, represents the inertial force, represents the damping force, It is the total mass of the model body and the spring when vibrating. The spring mass is included in 1 / 3 of the total spring mass. , are the acceleration and velocity of the model when it vibrates. is the damping coefficient when the model vibrates. The damping coefficient can be obtained by formula 2.

[0043] Formula 2 in, is the damping ratio of the model, which is approximately obtained by the free vibration of the model and the logarithmic attenuation method. is the overall stiffness of the model.

[0044] The preset displacement-force conversion relationship is the preset relationship between the longitudinal displacement of the model and the vertical force on the model. The process of determining the preset displacement-force conversion relationship is as follows: Figure 2b In the upper part of the target rigid segment model example diagram shown in the figure, the lateral displacement, vertical displacement, and angular displacement of the model after displacement are , , When the model is displaced, both sides of the model are considered to be displaced simultaneously, so only one side needs to be displaced. For the four springs used for the suspension on one side, is the original length of the spring, is the stiffness of a spring, , , , They are the total lengths of the springs after static stretching at the left suspension upper end, the right suspension upper end, the left suspension lower end, and the right suspension lower end. , , , They are the total length of the left suspension upper end, the right suspension upper end, the left suspension lower end, and the right suspension lower end. , , , They are the deformation of the springs after static stretching at the left suspension upper end, the right suspension upper end, the left suspension lower end, and the right suspension lower end. , , , They are the total suspension lengths of the left suspension upper end, the right suspension upper end, the left suspension lower end, and the right suspension lower end excluding spring deformation. , , , , , , , As shown in formula 3, Formula 3 In such Figure 2b In the upper part of the target stiffness segment model example shown, that is, for the four springs used on one side of the suspension, , , , are the lateral displacements of the four suspension points on one side in the plane, , , , They are the vertical displacements of the four suspension points on one side in the plane. , , , , , , , It can be expressed by Formula 4 to Formula 7.

[0045] Formula 4 Formula 5 Formula 6 Formula 7 in, Indicates the distance between the left and right suspensions. Indicates the distance between the upper and lower suspensions.

[0046] The conversion relationship between the displacement and force of the spring at the four suspension points on one side is obtained as shown in Formulas 8 to 12.

[0047] Formula 8 Formula 9 Formula 10 Formula 11 Formula 12 in, , , , are the forces after the displacement of the unilateral four-sided spring, , , , They are the angles between the single-sided four-sided spring and the vertical direction after displacement. , , , They are the vertical force components of the spring after the single-sided four-sided spring is displaced. , , , They are the moments of the spring on the center point of the model after the unilateral four-sided spring is displaced. , , After the model is displaced, the vertical force component, lateral force component and moment corresponding to the displacement are obtained. Thus, the vertical force component corresponding to the relative displacement time course can be determined according to the relative displacement time course and the conversion relationship between the preset displacement and force.

[0048] Step 104 , obtaining 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.

[0049] 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 formula 13.

[0050] Formula 13 in, Indicates aerodynamic force, represents the vertical component of force, represents the inertial force, Represents the damping force.

[0051] The solution of the present application is to collect target images of the target rigid segment model at multiple wind speeds after the target rigid segment model is in 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; for each wind speed, 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 according to the center position of the first target circle and the center position of the second target circle in the target image; 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 conversion relationship between the preset 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 series of the target rigid segment model based on the image, and determines the aerodynamic force of the target rigid segment model based on the vertical component force corresponding to the relative displacement time series, thereby avoiding the use of high-precision dynamometers to measure the aerodynamic force, thereby reducing the experimental cost and the difficulty of experimental installation. There is no need to repeatedly measure the aerodynamic force with high-precision dynamometers in repeated wind tunnel tests, thereby improving the experimental efficiency.

[0052] Figure 2a is another flow chart of the method for determining aerodynamic force provided by the present application. Figure 1 Based on the illustrated embodiment and various optional implementation schemes, the steps of obtaining the inertial force and damping force generated when the target rigid segment model vibrates are described in detail. Figure 2a As shown, the method may include the following steps: Step 201 : After the target rigid segment model vibrates in a steady state, target images of the target rigid segment model at multiple wind speeds are collected.

[0053] 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 position of the first target circle and the center position of the second target circle in the target image.

[0054] Step 203: Obtain the total mass and acceleration of the target rigid segment model during vibration.

[0055] Exemplarily, the total mass of the target rigid segment model when vibrating is m, and the acceleration is determined as a according to the time corresponding to the longitudinal displacement of the target rigid segment model when vibrating and the longitudinal displacement.

[0056] Step 204: determining the inertial force generated when the target rigid segment model vibrates according to the total mass and the acceleration.

[0057] Specifically, the total mass of the target rigid segment model during vibration is m, and the acceleration is a, and the inertial force can be obtained for =ma.

[0058] Step 205 , obtaining the speed of the target rigid segment model when it vibrates and the damping coefficient of the target rigid segment model.

[0059] For example, the speed v is determined according to the time corresponding to the longitudinal displacement of the target rigid segment model during vibration and the longitudinal displacement. The damping coefficient of the target rigid segment model can be obtained according to the damping ratio and 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 attenuation method.

[0060] Step 206 : determining the damping force generated when the target rigid segment model vibrates according to the speed and damping coefficient of the target rigid segment model when it vibrates.

[0061] Specifically, the damping ratio of the target rigid segment model is c, and the speed during vibration is v, and the damping force can be obtained for =cv.

[0062] Step 207, determining the vertical component force corresponding to the relative displacement time series according to the relative displacement time series and the preset conversion relationship between displacement and force.

[0063] Step 208 , obtaining 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.

[0064] The solution of the present application can more accurately determine the aerodynamic force by accurately calculating the inertial force and the damping force, thereby improving the reliability, safety and anti-interference ability of the experiment, optimizing the aerodynamic force determination effect, and the calculation is simple, thereby improving the experimental efficiency.

[0065] Figure 3 is a schematic diagram of the structure of the aerodynamic force determination device provided in the present application, and the device is suitable for executing the aerodynamic force determination method provided in the present application. Figure 3 As shown, the device may specifically include: The acquisition module 301 is used to acquire target images of the target rigid segment model under multiple wind speeds after the target rigid segment model is in 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.

[0066] The displacement time history determination module 302 is used to 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 position of the first target circle and the center position of the second target circle in the target image for each wind speed.

[0067] The component force determination module 303 is used 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 series according to the relative displacement time series and the conversion relationship between the preset displacement and force.

[0068] The aerodynamic force determination module 304 is used to obtain the aerodynamic force of the target rigid segment model according to the vertical force component, the inertial force and the damping force of the target rigid segment model.

[0069] In one embodiment, the device also includes: a center determination module, which is used to determine the diameter of the first target circle and the diameter of the second target circle according to the target image before the displacement time determination module 302 determines the relative displacement time 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; and determines 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.

[0070] In one embodiment, the displacement time course determination module 302 is specifically used 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 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; determine the relative displacement time course 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.

[0071] In one embodiment, the displacement time course determination module 302, in determining the relative displacement time course 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, is specifically used 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 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, and a conversion ratio between preset pixel coordinates and physical coordinates; determine the relative displacement time course 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.

[0072] In one embodiment, the component force determination module 303 is specifically used to determine the inertial force generated when the target rigid segment model vibrates by: obtaining the total mass and acceleration of the target rigid segment model when it vibrates; and determining the inertial force generated when the target rigid segment model vibrates based on the total mass and the acceleration.

[0073] In one embodiment, the component force determination module 303 is specifically used to determine the damping force generated when the target rigid segment model vibrates by: obtaining the speed of the target rigid segment model when it vibrates and the damping coefficient of the target rigid segment model; and determining the damping force generated when the target rigid segment model vibrates based on the speed of the target rigid segment model when it vibrates and the damping coefficient.

[0074] In one embodiment, the target rigid segment model also 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.

[0075] The device of the present application collects target images of the target rigid segment model under multiple wind speeds after the target rigid segment model vibrates in a steady state; 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, 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 according to the center position of the first target circle and the center position of the second target circle in the target image; 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 conversion relationship between the preset 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 series of the target rigid segment model based on the image, and determines the aerodynamic force of the target rigid segment model based on the vertical component force corresponding to the relative displacement time series, thereby avoiding the use of high-precision dynamometers to measure the aerodynamic force, thereby reducing the experimental cost and the difficulty of experimental installation. There is no need to repeatedly measure the aerodynamic force with high-precision dynamometers in repeated wind tunnel tests, thereby improving the experimental efficiency.

[0076] The present application also provides an electronic device, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, the aerodynamic force determination method provided in any of the above embodiments is implemented.

[0077] The present application also provides a computer-readable medium having a computer program stored thereon, and when the program is executed by a processor, the aerodynamic force determination method provided in any of the above embodiments is implemented.

[0078] Reference below Figure 4 , which shows a structural schematic 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 bring any limitation to the function and scope of use of the present application.

[0079] like Figure 4As shown, the electronic device 400 includes a central processing unit (CPU) 401, which 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 part 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, the ROM 402, and the 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.

[0080] 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 needed. A removable medium 411, such as a magnetic disk, an optical disk, a magneto-optical disk, a semiconductor memory, etc., is installed on the drive 410 as needed, so that a computer program read therefrom is installed into the storage section 408 as needed.

[0081] In particular, according to the embodiments disclosed in the present application, the process described above with reference to the flowchart can be implemented as a computer software program. For example, the embodiments disclosed in the present application include a computer program product, which includes a computer program carried on a computer-readable medium, and the computer program contains program code for executing the method shown in the flowchart. In such an embodiment, the computer program can be downloaded and installed from the network through the communication part 409, and / or installed from the removable medium 411. When the computer program is executed by the central processing unit (CPU) 401, the above-mentioned functions defined in the system of the present application are executed.

[0082] It should be noted that the computer-readable medium shown in the present application may be a computer-readable signal medium or a computer-readable storage medium or any combination of the above two. The computer-readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device or device, or any combination of the above. More specific examples of computer-readable storage media may 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 the present application, a computer-readable storage medium may be any tangible medium containing or storing a program that can be used by or in combination with an instruction execution system, device or device. In the present application, a computer-readable signal medium may include a data signal propagated in a baseband or as part of a carrier wave, which carries a computer-readable program code. This propagated data signal may take a variety of forms, including but not limited to electromagnetic signals, optical signals, or any suitable combination of the above. Computer-readable signal media may also be any computer-readable medium other than computer-readable storage media, which may 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 the computer-readable medium may be transmitted using any appropriate medium, including but not limited to: wireless, wire, optical cable, RF, etc., or any suitable combination of the above.

[0083] The flow chart and block diagram in the accompanying drawings illustrate the possible architecture, function and operation of the system, method and computer program product according to various embodiments of the present application. In this regard, each box in the flow chart or block diagram can represent a module, a program segment or a part of a code, and the above-mentioned module, program segment or a part of a code contains one or more executable instructions for realizing the specified logical function. It should also be noted that in some alternative implementations, the functions marked in the box can also occur in a different order from the order marked in the accompanying drawings. For example, two boxes represented in succession can actually be executed substantially in parallel, and they can sometimes be executed in the opposite order, depending on the functions involved. It should also be noted that each box in the block diagram or flow chart, and the combination of the boxes in the block diagram or flow chart can be implemented with a dedicated hardware-based system that performs a specified function or operation, or can be implemented with a combination of dedicated hardware and computer instructions.

[0084] The modules and / or units described in this application may be implemented in software or hardware. The modules and / or units described may also be set in a processor, for example, it may be described as: a processor includes an acquisition module, a displacement time determination module, a component force determination module, and an aerodynamic force determination module. The names of these modules do not, in some cases, constitute limitations on the modules themselves.

[0085] As another aspect, the present application also provides a computer-readable medium, which may be included in the device described in the above embodiment; or may exist independently without being assembled into the device. The above computer-readable medium carries one or more programs, and when the above one or more programs are executed by a device, the device performs the following operations: After the target rigid segment model is in steady-state vibration, target images of the target rigid segment model are collected 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, 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 according to the center position of the first target circle and the center position of the second target circle in the target image; 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 conversion relationship between the preset 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.

[0086] According to the technical solution of the present application, after the target rigid segment model vibrates in a steady state, 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, 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 according to the center position of the first target circle and the center position of the second target circle in the target image; 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 conversion relationship between the preset 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 series of the target rigid segment model based on the image, and determines the aerodynamic force of the target rigid segment model based on the vertical component force corresponding to the relative displacement time series, thereby avoiding the use of high-precision dynamometers to measure the aerodynamic force, thereby reducing the experimental cost and the difficulty of experimental installation. There is no need to repeatedly measure the aerodynamic force with high-precision dynamometers in repeated wind tunnel tests, thereby improving the experimental efficiency.

[0087] An embodiment of the present application also provides a computer program product, including a computer program, which, when executed by a processor, implements the aerodynamic force determination method provided in any embodiment of the present application.

[0088] In the process of implementation, the computer program product can be written in one or more programming languages ​​or a combination thereof to perform the computer program code of the present application, and the programming language includes an object-oriented programming language, such as Java, Smalltalk, C++, and also includes a conventional procedural programming language, such as "C" language or similar programming language. The program code can be executed completely on the user's computer, partially on the user's computer, as an independent software package, partially on the user's computer and partially on the remote computer, or completely on the 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, using an Internet service provider to connect through the Internet).

[0089] It should be understood that the various forms of processes shown above can be used to reorder, add or delete steps. For example, the steps recorded in this application can be executed in parallel, sequentially or in different orders, as long as the expected results of the technical solution of this application can be achieved, and this document is not limited here.

[0090] Although the present invention has been described with reference to preferred embodiments, various modifications may be made thereto and parts thereof may be replaced by equivalents without departing from the scope of the present invention. In particular, the various technical features mentioned in the various embodiments may be combined in any manner as long as there are no structural conflicts. The present invention is not limited to the specific embodiments disclosed herein, but includes all technical solutions falling within the scope of the claims.

Claims

1. A method for determining aerodynamic force, characterized in that: The method comprises: After the target rigid segment model vibrates in a steady state, 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, determining a relative displacement time history between a target rigid segment model at a current wind speed and a target rigid segment model at a target wind speed according to a center position of the first target circle and a center position of 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 a conversion relationship between a preset displacement and force; The aerodynamic force of the target rigid segment model is obtained according to the vertical component force, the inertial force of the target rigid segment model and the damping force.

2. The method according to claim 1, characterized in that 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; The center position of the first target circle and the center position of the second target circle are determined according to the diameter of the first target circle and the diameter of the second target circle.

3. The method according to claim 2, characterized in that 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 includes: 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; 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 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.

4. The method according to claim 3, characterized in that 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 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, comprises: 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 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, and a conversion ratio between the preset pixel coordinates and the physical coordinates; 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 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.

5. The method according to claim 1, characterized in that The determining of the inertial force generated when the target rigid segment model vibrates includes: Obtain the total mass and acceleration of the target rigid segment model during vibration; The inertial force generated when the target rigid segment model vibrates is determined according to the total mass and the acceleration.

6. The method according to claim 1, characterized in that Determining the damping force generated when the target rigid segment model vibrates includes: Acquiring the speed of the target rigid segment model when it vibrates and the damping coefficient of the target rigid segment model; The damping force generated when the target rigid segment model vibrates is determined according to the speed of the target rigid segment model when it vibrates and the damping coefficient.

7. The method according to claim 1, characterized in that The target rigid segment model also 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 embedded in the two 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 springs are connected to the upper ends of the end plates, and the upper ends of some 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.

8. An aerodynamic force determination device, characterized in that: The device comprises: An acquisition module is used to acquire target images of the target rigid segment model at multiple wind speeds after the target rigid segment model vibrates in a steady state; 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, for determining, for each wind speed, a relative displacement time history between a target rigid segment model at a current wind speed and a target rigid segment model at a target wind speed according to a center position of the first target circle and a center position of the second target circle in the target image; A component force determination module, used 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 series according to the relative displacement time series and a conversion relationship between a preset displacement and force; The aerodynamic force determination module is used 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.

9. An electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein: When the processor executes the program, the aerodynamic force determination method according to any one of claims 1 to 7 is implemented.

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

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