CN119915477B - Aerodynamic force determining method and device, electronic equipment and storage medium - Google Patents
Aerodynamic force determining method and device, electronic equipment and storage medium Download PDFInfo
- Publication number
- CN119915477B CN119915477B CN202510400532.2A CN202510400532A CN119915477B CN 119915477 B CN119915477 B CN 119915477B CN 202510400532 A CN202510400532 A CN 202510400532A CN 119915477 B CN119915477 B CN 119915477B
- Authority
- CN
- China
- Prior art keywords
- target
- circle
- center
- rigid segment
- target circle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
本发明提供一种气动力确定方法、装置、电子设备及存储介质，涉及斜拉桥技术领域，方法包括：在目标刚性节段模型稳态振动后，采集目标刚性节段模型在多个风速下的标靶图像；针对每一个风速，根据标靶图像中第一目标圆的圆心位置以及第二目标圆的圆心位置，确定在当前风速下目标刚性节段模型与目标风速下目标刚性节段模型之间的相对位移时程；根据相对位移时程以及预设位移与力的转换关系确定相对位移时程对应的竖向分力；根据竖向分力、目标刚性节段模型的惯性力以及阻尼力得到目标刚性节段模型的气动力。即本申请的方案，避免了使用高精度的测力计对气动力进行测量，从而降低了实验成本，并且降低了实验的安装难度，进而提升了实验效率。
The present invention provides an aerodynamic force determination method, device, electronic device and storage medium, which relates to the technical field of cable-stayed bridges. The method includes: after the target rigid segment model is in steady-state vibration, collecting target images of the target rigid segment model at multiple wind speeds; 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, 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; determining 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; 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 the use of a high-precision dynamometer to measure the aerodynamic force, thereby reducing the experimental cost, and reducing the difficulty of experimental installation, thereby improving the experimental efficiency.
Description
Technical Field
The present invention relates to the technical field of cable-stayed bridges, and in particular, to a aerodynamic force determining method, a device, an electronic device, and a storage medium.
Background
Stay cables are the most important load bearing members of cable-stayed bridges, and the performance of the stay cables directly affects the overall safety of the bridge. Under the action of incoming wind, the stay cable (also called a cable) can cause periodic change of the surface air pressure of the cable, so that periodic aerodynamic force is generated on the surface of the cable. When the frequency of aerodynamic force is close to or equal to the frequency of certain-order natural vibration of the inhaul cable, vortex-induced resonance can occur to the inhaul cable. And further, fatigue damage of the anchoring end of the inhaul cable is possibly caused, or a corrosion protection system at the end part of the inhaul cable is damaged, so that the service life of the inhaul cable is shortened. Therefore, the method has important significance for the design and maintenance of the inhaul cable by calculating the generation mechanism of the inhaul cable vortex-induced resonance, namely aerodynamic force.
At present, in a wind tunnel test, a high-precision force transducer is adopted to obtain aerodynamic force of a guy cable rigid model.
However, in the wind tunnel test, the high-precision load cell is high in cost, complex to install in the test and low in test efficiency.
Disclosure of Invention
The invention aims to solve the technical problems of overcoming the defects of the prior art and providing a aerodynamic force determining method, a aerodynamic force determining device, electronic equipment and a storage medium, so as to solve the problems of high cost, complex installation in experiments and low experimental efficiency of high-precision force sensors in wind tunnel tests in the prior art.
In order to solve the technical problems, the technical scheme provided by the invention is as follows:
in a first aspect, the present application provides a method of aerodynamic force determination, the method comprising:
After a target rigid segment model vibrates in a steady state, acquiring target images of the target rigid segment model at a plurality of wind speeds, wherein the target of the target rigid segment model comprises a first target circle, a second target circle and a cross mark, the cross mark is positioned 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 larger than that of the second target circle;
determining a relative displacement time interval between a target rigid segment model and a target rigid segment model at a current wind speed according to the circle center position of the first target circle and the circle center position of the second target circle in the target image for each wind speed;
Determining an inertial force and a damping force generated when the target rigid segment model vibrates, and determining a vertical component corresponding to the relative displacement time interval according to the relative displacement time interval and a conversion relation between preset displacement and force;
And obtaining 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.
In a second aspect, the present application provides a aerodynamic force determination device, the device comprising:
The system comprises an acquisition module, a target rigidity section model, a target acquisition module and a control module, wherein the acquisition module is used for acquiring target images of the target rigidity section model at a plurality of wind speeds after the target rigidity section model is in steady-state vibration, the target of the target rigidity section model comprises a first target circle, a second target circle and a cross mark, the cross mark is positioned 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 larger than the radius of the second target circle;
The displacement time interval determining module is used for determining relative displacement time intervals between the target rigid segment model and the target rigid segment model under the current wind speed according to the circle center position of the first target circle and the circle center position of the second target circle in the target image for each wind speed;
The component force determining module is used for determining an inertia force and a damping force generated when the target rigid segment model vibrates, and determining a vertical component force corresponding to the relative displacement time according to the relative displacement time and the conversion relation between the preset displacement and the force;
And the aerodynamic force determining module is used for obtaining aerodynamic force of the target rigid segment model according to the vertical component force, the inertia force and the damping force of the target rigid segment model.
In a third aspect, the present application provides an electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, the processor implementing a aerodynamic force determination method according to any of the embodiments of the present application when executing the program.
In a fourth aspect, the present application provides a computer readable storage medium having stored thereon a computer program which when executed by a processor implements a aerodynamic force determination method according to any of the embodiments of the present application.
In a fifth aspect, the application provides a computer program product comprising a computer program which, when executed by a processor, implements a aerodynamic force determination method according to any embodiment of the application.
Compared with the prior art, the method has the advantages that after a target rigid segment model is vibrated in a steady state, target images of the target rigid segment model at a plurality of wind speeds are acquired, wherein the targets of the target rigid segment model comprise 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, the radius of the first target circle is larger than the radius of the second target circle, for each wind speed, the relative displacement time interval between the target rigid segment model and the target rigid segment model at the current 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 images, the inertia force and the damping force generated when the target rigid segment model vibrates are determined, the vertical component corresponding to the relative displacement time interval is determined according to the relative displacement time interval and the conversion relation between the preset displacement and the force, and the aerodynamic force of the target rigid segment model is obtained according to the vertical component, the inertia force and the damping force of the target rigid segment model. According to the scheme, the relative displacement time interval 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 interval, so that the aerodynamic force is prevented from being measured by using a high-precision dynamometer, the experimental cost is reduced, the installation difficulty of an experiment is reduced, the aerodynamic force is not required to be measured repeatedly by the high-precision dynamometer in a repeated wind tunnel experiment, and the experimental efficiency is further improved.
Drawings
The invention will be described in more detail hereinafter on the basis of embodiments and with reference to the accompanying drawings. Wherein:
FIG. 1 is a schematic flow chart of a aerodynamic force determination method provided by the application;
FIG. 2a is another flow chart of the aerodynamic force determination method provided by the present application;
FIG. 2b is an exemplary diagram of a target rigid segment model of the aerodynamic force determination method provided by the present application;
FIG. 3 is a schematic view of a aerodynamic force determination device according to the present application;
FIG. 4 is a schematic diagram of an electronic device according to the present application;
reference numerals:
1-spring, 2-model body, 3-end plate, 4-target.
Detailed Description
The invention will now be described in further detail with reference to the drawings and the specific examples, which are not intended to limit the scope of the invention.
In the description of the present invention, it should be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientation or positional relationships shown in the drawings, merely to facilitate describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed, mechanically connected, electrically connected, directly connected, indirectly connected via an intervening medium, or in communication between two elements or in an interaction relationship between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
The invention is described in further detail below with reference to the drawings and specific examples of the specification.
Fig. 1 is a schematic flow chart of a aerodynamic force determining method provided by the present application, which may be performed by an aerodynamic force determining device, and the device may be implemented in software and/or hardware. In a specific embodiment, the apparatus may be applied in an electronic device, which may be a computer. The following embodiments will be described taking the application of the apparatus in an electronic device as an example, and referring to fig. 1, the method may specifically include the following steps:
Step 101, after steady-state vibration of the target rigid segment model, target images of the target rigid segment model at a plurality of wind speeds are acquired.
The target of the target rigid segment model comprises a first target circle, a second target circle and a cross mark, wherein the cross mark is positioned 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 larger than that of the second target circle.
Specifically, the target rigid segment model is a model capable of simulating the stress condition of the cable-stayed bridge. A section of the target rigid segment model is affixed with a target for determining movement of the target rigid segment model in a vertical direction. The target is formed by a big circle and a small circle, the target is attached to the side surface of the model, and the center of the cross section of the model is aligned with the cross mark in the target. An acquisition device, such as an industrial camera, for acquiring target images of a target rigid segment model at a plurality of wind speeds is erected outside a wind tunnel test chamber and faces the target position through transparent glass so as to shoot the target images. After the target rigid segment model enters steady-state vibration under the influence of any wind speed, the industrial camera acquires a plurality of target images at a plurality of wind speeds according to a preset camera sampling frequency. And carrying out statistical parameter calculation on the data of the plurality of target images, and taking the statistical parameter result as the data in the subsequent step so as to improve the accuracy of the acquisition result.
Optionally, the target rigid segment model further comprises a spring suspension system, a model body and more than two end plates, wherein the target is attached to the model body, the center of the face where the width and the height of the model body are located coincides with the center of the target, the end plates are respectively nested at two ends of the model body to enable the model body to be located between the two end plates, the spring suspension system comprises a plurality of springs, the lower ends of part of the springs are connected with the upper ends of the end plates, and the upper ends of part of the springs are connected with the lower ends of the end plates to enable the model body between the end plates and the end plates to be suspended.
Specifically, fig. 2b is an exemplary diagram of a target rigid segment model of the aerodynamic force determination method provided by the present application. As shown in fig. 2b, the spring suspension system comprises 8 springs 1, wherein the lower ends of 4 springs 1 are each connected to the upper end of the end plate 3, and the upper ends of the other 4 springs 1 are each connected to the lower end of the end plate 3 to suspend the end plate 3 and the mould body 2 between the end plates 3. The model body 2 of the rigid segment model is obtained after the cable-stayed bridge is contracted according to a preset contraction scale ratio. The number of end plates 3 is two. 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 two ends of the model body 2, so that the model body 2 is positioned between the two end plates 3.
Step 102, determining a relative displacement time interval between the target rigid segment model and the target rigid segment model at the current 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.
Wherein the target wind speed is a value set according to actual demand, and the target wind speed may be 0, for example.
Specifically, the displacement time refers to the displacement change condition of the object in a preset time, and the displacement is plotted usually with time as an abscissa and displacement as an ordinate. The relative displacement time course in this embodiment is a relative difference value capable of representing the displacement change condition of the target rigid segment model at the current wind speed and the displacement change condition of the target rigid segment model at the target wind speed, for example, the displacement time course curve of the target rigid segment model at the current wind speed and the displacement time course curve of the target rigid segment model at the target wind speed are subtracted in the same time, and the obtained curve is the relative displacement time course between the target rigid segment model at the current wind speed and the target rigid segment model at the target wind speed. And determining the relative displacement time course between the target rigid segment model and the target rigid segment model at the current wind speed according to the circle center position of the first target circle and the movement condition of the circle center position of the second target circle relative to the wind speed 0 in the experiment, namely the displacement time course caused by the vertical component force when the model vibrates.
Optionally, before determining the relative displacement time interval 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, steps 21 to 22 may be further performed.
Step 21, determining the diameter of the first target circle and the diameter of the second target circle according to the target image.
Specifically, the images acquired at different wind speeds are processed by adopting an edge detection algorithm, and the diameter of the first target circle and the diameter of the second target circle are obtained by detecting the edges of the second target circle of the first target circle.
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.
Specifically, the images acquired at different wind speeds are processed by adopting an edge detection algorithm, and the center position of the first target circle and the center position of the second target circle are obtained by detecting the edges of the second target circle of the first target circle.
Optionally, after performing steps 21 to 22, determining the relative displacement time interval 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 may be implemented through steps 1021 to 1022.
And 1021, 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.
Step 1022, determining the relative displacement time interval 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.
Specifically, the pixel coordinates are converted into physical coordinates through a preset proportional relationship, and the relative displacement time interval of each wind speed relative to the model at 0 wind speed is obtained.
Alternatively, step 1022 may be implemented by steps 221 through 222.
Step 221, obtaining physical coordinates of the diameter of the first target circle, physical coordinates of the diameter of the second target circle, physical coordinates of the center of the first target circle and 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 center of the second target circle, the pixel coordinates of the center of the first target circle and the conversion ratio of the preset pixel coordinates and the physical coordinates.
Step 222, determining a relative displacement time interval 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.
For example, edge detection processes each picture to obtain edge pixel points of a first target circle and a second target circle, and takes the maximum distance between the edge pixel points of the respective areas of the first target circle and the second target circle as the diameter and the center of two points of the maximum distance as the circle center. The preset conversion proportion relation between the pixel coordinates and the physical coordinates is that the relative vertical displacement (taking pixels as a unit) of each wind speed compared with a model of 0 wind speed is respectively. Relative vertical displacement of its physical coordinatesThe relative vertical displacement change condition in a period of time can be expressed as the relative vertical displacement time course.
Wherein, the Is the physical size of each pixel. For example, the physical size of the pixel may be 0.1mm.
And 103, determining the inertia force and the damping force of the target rigid segment model, and determining the vertical component force corresponding to the relative displacement time course according to the relative displacement time course and the conversion relation between the preset displacement and the force.
Specifically, the inertial force of the target rigid segment model is the inertial force caused by the total mass of the model body and a part of the springs during vibration, and the mass of the springs accounts for 1/3 of the total mass of the springs, for example. The damping force is the model damping force obtained according to the speed of the model vibration and the damping ratio of the model. The inertial force and damping force of the model can be determined by equation 1.
Equation 1
Wherein, the The force of inertia is indicated as such,The damping force is indicated as such,The mass of the spring is counted as 1/3 of the total mass of the model body and the spring when vibrating.,Acceleration and velocity of the model during vibration are respectively.Is the damping coefficient of the model when vibrating. The damping coefficient can be obtained from equation 2.
Equation 2
Wherein, the The damping ratio of the model is obtained by the free vibration of the model and the logarithmic attenuation method,Is the overall stiffness of the model.
The conversion relation between the preset displacement and the force is the preset relation between the longitudinal displacement of the model and the vertical force applied by the model. The conversion relation between the preset displacement and the force is determined by respectively determining the lateral displacement, the vertical displacement and the corner displacement after the displacement of the model in the upper half part of the model illustration of the target rigid segment as shown in figure 2b、、. When the model is displaced, both sides of the model are regarded as being displaced integrally at the same time, so that only one side is required to be seen for displacement. For 4 springs for hanging single side, there areIs the original length of the spring,Is the stiffness of one of the springs,、、、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 after the springs are statically stretched is respectively.、、、The total suspension length of the left suspension upper end, the right suspension upper end, the left suspension lower end and the right suspension lower end is respectively.、、、The deformation amounts of the left suspension upper end, the right suspension upper end, the left suspension lower end and the right suspension lower end after the springs are statically stretched are respectively.、、、The total suspension length of the left suspension upper end, the right suspension upper end, the left suspension lower end and the right suspension lower end which do not contain the deformation of the spring is respectively.、、、、、、、As shown in the formula 3 of the drawings,
Equation 3
In the upper half of the example diagram of the target rigid segment model shown in fig. 2b, i.e. for the 4 springs used on one side of the suspension,、、、Respectively the lateral displacement of the four hanging points on one side in the plane,、、、The vertical displacement of the four hanging points on one side in the plane is respectively generated.、、、、、、、Can be represented by formulas 4 to 7.
Equation 4
Equation 5
Equation 6
Equation 7
Wherein, the Indicating the distance between the left and right suspension,Representing the distance between the upper and lower suspensions.
The conversion of the displacement of the spring at the four suspension points on one side with force is shown in the formulas 8 to 12.
Equation 8
Equation 9
Equation 10
Equation 11
Equation 12
Wherein, the 、、、The forces after the single-side four-side springs are displaced,、、、Respectively the included angles between the single-side four-side springs and the vertical direction after the single-side four-side springs are displaced.、、、The components of the vertical change of the springs after the single-side four-side springs are displaced are respectively shown.、、、The moment of the spring at the center point of the model after the single-side four-side spring is displaced is respectively shown.、、After the models are respectively displaced, the vertical component force, the horizontal component force and the moment corresponding to the displacement are generated. Therefore, the vertical component force corresponding to the relative displacement time interval can be determined according to the relative displacement time interval and the conversion relation between the preset displacement and the force.
And 104, obtaining 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.
Specifically, after the vertical component force, the inertia force and the damping force of the target rigid segment model are obtained, aerodynamic force can be obtained by subtracting the inertia force and the damping force from the vertical component force. That is, aerodynamic force can be determined by equation 13.
Equation 13
Wherein, the Represents the aerodynamic force of the air, and the air is compressed,Represents a vertical component of force,The force of inertia is indicated as such,Representing the damping force.
The method comprises the steps of collecting target images of a target rigid segment model at a plurality of wind speeds after the target rigid segment model is vibrated in a steady state, determining relative displacement time intervals between the target rigid segment model and the target rigid segment model at the current wind speed according to the position of the center of the first target circle and the position of the center of the second target circle in the target image, determining inertial force and damping force generated when the target rigid segment model vibrates, determining vertical component force corresponding to the relative displacement time intervals according to the relative displacement time intervals and the conversion relation between preset displacement and force, and obtaining aerodynamic force of the target rigid segment model according to the vertical component force, the force of the target rigid segment model and the damping force. According to the scheme, the relative displacement time interval 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 interval, so that the aerodynamic force is prevented from being measured by using a high-precision dynamometer, the experimental cost is reduced, the installation difficulty of an experiment is reduced, the aerodynamic force is not required to be measured repeatedly by the high-precision dynamometer in a repeated wind tunnel experiment, and the experimental efficiency is further improved.
Fig. 2a is another flow chart of the aerodynamic force determining method provided by the present application, and this embodiment describes in detail the steps of obtaining inertial force and damping force generated when the target rigid segment model vibrates based on the embodiment shown in fig. 1 and various alternative implementations. As shown in fig. 2a, the method may comprise the steps of:
Step 201, after steady-state vibration of the target rigid segment model, acquiring target images of the target rigid segment model at a plurality of wind speeds.
Step 202, determining a relative displacement time interval between the target rigid segment model and the target rigid segment model at the current 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.
Step 203, obtaining the total mass and acceleration of the target rigid segment model during vibration.
For example, the total mass of the target rigid segment model when vibrating is m, and the acceleration is determined to be a according to the time corresponding to the longitudinal displacement of the target rigid segment model when vibrating and the longitudinal displacement.
And 204, determining the inertia force generated when the target rigid segment model vibrates according to the total mass and the acceleration.
Specifically, the total mass of the target rigid segment model during vibration is m, the acceleration is a, and the inertia force can be obtainedIs that=ma。
Step 205, obtaining the speed of the target rigid segment model when vibrating and the damping coefficient of the target rigid segment model.
Illustratively, the velocity v is determined from the time corresponding to the longitudinal displacement of the target rigid segment model as it vibrates and the longitudinal displacement. 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 and logarithmic attenuation method of the model.
And 206, determining the damping force generated when the target rigid segment model vibrates according to the speed and the damping coefficient when the target rigid segment model vibrates.
Specifically, the damping ratio of the target rigid segment model is c, and the speed during vibration is v, so that the damping force can be obtainedIs that=cv。
Step 207, determining a vertical component corresponding to the relative displacement time interval according to the relative displacement time interval and the conversion relation between the preset displacement and the force.
And step 208, obtaining aerodynamic force of the target rigid segment model according to the vertical component force, the inertia force and the damping force of the target rigid segment model.
According to the scheme, the aerodynamic force can be determined more accurately by accurately calculating the inertia force and the damping force, so that the reliability, the safety and the anti-interference capability of an experiment are improved, the aerodynamic force determining effect is optimized, the calculation is simple, and the experiment efficiency is improved.
Fig. 3 is a schematic structural view of a aerodynamic force determining device provided by the present application, which is suitable for executing the aerodynamic force determining method provided by the present application. As shown in fig. 3, the apparatus may specifically include:
The acquisition module 301 is configured to acquire target images of a target rigid segment model at a plurality of wind speeds after the target rigid segment model is in steady-state vibration, where 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 a center of the target, a distance between a center of the first target circle and a center of the target is equal to a distance between a center of the second target circle and a center of the target, and a radius of the first target circle is larger than a radius of the second target circle.
The displacement time interval determining module 302 is configured to determine, for each wind speed, a relative displacement time interval 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 component force determining module 303 is configured to determine an inertial force and a damping force generated when the target rigid segment model vibrates, and determine a vertical component force corresponding to the relative displacement time interval according to the relative displacement time interval and a conversion relationship between a preset displacement and a force.
The aerodynamic force determining module 304 is configured to obtain 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.
In one embodiment, the device further comprises a circle center determining module, configured to determine, according to the target image, a diameter of the first target circle and a diameter of the second target circle before the displacement time interval determining module 302 determines the relative displacement time interval 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 circle center position of the first target circle and the circle center position of the second target circle in the target image, and determine, according to the diameter of the first target circle and the diameter of the second target circle, the circle center position of the first target circle and the circle center position of the second target circle.
In one embodiment, the displacement time interval determining module 302 is specifically configured to determine the relative displacement time interval of the wind speed with respect to the target wind speed 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, and determine the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the diameter of the second target circle, the center of the first target circle, and the center of the second target circle, and according to the diameter of the first target circle, the pixel coordinates of the second target circle, the center of the first target circle, and the center of the second target circle.
In one embodiment, the displacement schedule determining module 302 is configured to determine a relative displacement schedule of the wind speed with respect to the target wind speed according to the pixel coordinate of the diameter of the first target circle, the pixel coordinate of the diameter of the second target circle, the pixel coordinate of the center of the first target circle, the pixel coordinate of the center of the second target circle, the pixel coordinate of the diameter of the first target circle, the physical coordinate of the center of the second target circle, and the conversion ratio of the preset pixel coordinate to the physical coordinate, and determine the relative displacement of the wind speed with respect to the target wind speed according to the physical coordinate of the diameter of the first target circle, the physical coordinate of the center of the second target circle, the physical coordinate of the center of the first target circle, and the physical coordinate of the second target wind speed.
In one embodiment, the component force determining module 303 is specifically configured to obtain a total mass and an acceleration of the target rigid segment model when the target rigid segment model vibrates, and determine an inertial force generated when the target rigid segment model vibrates according to the total mass and the acceleration.
In one embodiment, the component force determining module 303 is specifically configured to obtain a speed of the target rigid segment model when vibrating and a damping coefficient of the target rigid segment model, and determine the damping force generated when the target rigid segment model vibrates according to the speed of the target rigid segment model and the damping coefficient.
In one embodiment, the target rigid segment model further comprises a spring suspension system, a model body and more than two end plates, the target is attached to the model body, the centers of the faces where the width and the height of the model body are located are coincident with the centers of the target, the end plates are respectively nested at two ends of the model body, the model body is located between the two end plates, the spring suspension system comprises a plurality of springs, the lower ends of part of the springs are connected with the upper ends of the end plates, and the upper ends of part of the springs are connected with the lower ends of the end plates, so that the model body between the end plates and the end plates is suspended.
The device comprises a target rigid segment model, wherein a target of the target rigid segment model comprises a first target circle, a second target circle and a cross mark, the cross mark is positioned 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, the radius of the first target circle is larger than the radius of the second target circle, for each wind speed, the relative displacement time interval between the target rigid segment model and the target rigid segment model at the current 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 inertia force and the damping force generated when the target rigid segment model vibrates are determined, the vertical component corresponding to the relative displacement time interval is determined according to the relative displacement time interval and the conversion relation between the preset displacement and the force, and the aerodynamic force of the target rigid segment model is obtained according to the vertical component, the force of the target rigid segment model and the damping force. According to the scheme, the relative displacement time interval 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 interval, so that the aerodynamic force is prevented from being measured by using a high-precision dynamometer, the experimental cost is reduced, the installation difficulty of an experiment is reduced, the aerodynamic force is not required to be measured repeatedly by the high-precision dynamometer in a repeated wind tunnel experiment, and the experimental efficiency is further improved.
The application also provides an electronic device, which comprises a memory, a processor and a computer program stored on the memory and capable of running on the processor, wherein the processor realizes the aerodynamic force determining method provided by any embodiment when executing the program.
The present application also provides a computer readable medium having stored thereon a computer program which when executed by a processor implements the aerodynamic force determination method provided by any of the above embodiments.
Referring now to fig. 4, a schematic diagram of an electronic device 400 suitable for use in implementing the present application is shown. The electronic device shown in fig. 4 is only an example and should not impose any limitation on the functionality and scope of use of the present application.
As shown in fig. 4, 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 section 408 into a Random Access Memory (RAM) 403. In the RAM 403, various programs and data necessary for the operation of the electronic device 400 are also stored. The CPU 401, ROM 402, and RAM 403 are connected to each other by a bus 404. An input/output (I/O) interface 405 is also connected to bus 404.
Connected to the I/O interface 405 are an input section 406 including a keyboard, a mouse, and the like, an output section 407 including a Cathode Ray Tube (CRT), a Liquid Crystal Display (LCD), and the like, a speaker, and the like, a storage section 408 including a hard disk, and the like, and a communication section 409 including a network interface card such as a LAN card, a modem, and the like. The communication section 409 performs communication processing via a network such as the internet. The 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, or the like is installed on the drive 410 as needed, so that a computer program read therefrom is installed into the storage section 408 as needed.
In particular, according to embodiments of the present disclosure, the processes described above with reference to flowcharts may be implemented as computer software programs. For example, embodiments of the present disclosure include a computer program product comprising a computer program embodied on a computer readable medium, the computer program comprising program code for performing the method shown in the flow chart. In such an embodiment, the computer program may be downloaded and installed from a network via the communication portion 409 and/or installed from the removable medium 411. The above-described functions defined in the system of the present application are performed when the computer program is executed by a Central Processing Unit (CPU) 401.
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 two. The computer readable storage medium can be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or a combination of any of the foregoing. More specific examples of a computer-readable storage medium may include, but are not limited to, an electrical connection having one or more wires, a portable computer diskette, 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 disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing. In the context of this document, a computer readable storage medium may be any tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device. In the present application, however, the computer-readable signal medium may include a data signal propagated in baseband or as part of a carrier wave, with the computer-readable program code embodied therein. Such a propagated data signal may take any of a variety of forms, including, but not limited to, electro-magnetic, optical, or any suitable combination of the foregoing. A computer readable signal medium may also be any computer readable medium that is not a computer readable storage medium and that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device. Program code embodied on a computer readable medium may be transmitted using any appropriate medium, including but not limited to wireless, wireline, optical fiber cable, RF, etc., or any suitable combination of the foregoing.
The flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present application. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams or flowchart illustration, and combinations of blocks in the block diagrams or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
The modules and/or units described in the present application may be implemented in software or in hardware. The described modules and/or units may also be provided in a processor, which may be described as, for example, a processor comprising an acquisition module, a displacement time-course determination module, a component force determination module, and a aerodynamic force determination module. The names of these modules do not constitute a limitation on the module itself in some cases.
As a further aspect, the application also provides a computer readable medium which may be comprised in the device described in the above embodiments or may be present alone without being fitted into the device. The computer readable medium carries one or more programs which, when executed by one of the devices, cause the device to:
The method comprises the steps of collecting target images of a target rigid segment model at a plurality of wind speeds after the target rigid segment model is vibrated in a steady state, wherein the target of the target rigid segment model comprises 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, the radius of the first target circle is larger than the radius of the second target circle, for each wind speed, determining relative displacement time ranges between the target rigid segment model and the target rigid segment model at the current 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, determining inertia force and damping force generated when the target rigid segment model vibrates, determining vertical component force corresponding to the relative displacement time ranges according to the relative displacement time ranges and the conversion relation between preset displacement and force, and the damping force, and obtaining aerodynamic force of the target rigid segment model according to the vertical component force and the inertia force and the damping force of the target rigid segment model.
According to the technical scheme, after a target rigid segment model is vibrated in a stable state, target images of the target rigid segment model at a plurality of wind speeds are acquired, wherein the target of the target rigid segment model comprises a first target circle, a second target circle and a cross mark, the cross mark is positioned 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, the radius of the first target circle is larger than the radius of the second target circle, for each wind speed, the relative displacement time interval between the target rigid segment model and the target rigid segment model at the current 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 inertia force and the damping force generated when the target rigid segment model vibrates are determined, the vertical component corresponding to the relative displacement time interval is determined according to the relative displacement time interval and the conversion relation between the preset displacement and the force, and the aerodynamic force of the target rigid segment model is obtained according to the vertical component, the inertia force and the damping force of the target rigid segment model. According to the scheme, the relative displacement time interval 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 interval, so that the aerodynamic force is prevented from being measured by using a high-precision dynamometer, the experimental cost is reduced, the installation difficulty of an experiment is reduced, the aerodynamic force is not required to be measured repeatedly by the high-precision dynamometer in a repeated wind tunnel experiment, and the experimental efficiency is further improved.
Embodiments of the present application also provide a computer program product comprising a computer program which, when executed by a processor, implements a aerodynamic force determination method as provided by any of the embodiments of the present application.
Computer program product in the implementation, the computer program code for carrying out operations of the present application may be written in one or more programming languages, including an object oriented programming language such as Java, smalltalk, C ++ and conventional procedural programming languages, such as the "C" programming language or similar programming languages. The program code may execute entirely on the user's computer, partly on the user's computer, as a stand-alone software package, partly on the user's computer and partly on a remote computer or entirely on the remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer through any kind of network, including a Local Area Network (LAN) or a Wide Area Network (WAN), or may be connected to an external computer (for example, through the Internet using an Internet service provider).
It should be appreciated that various forms of the flows shown above may be used to reorder, add, or delete steps. For example, the steps described in the present application may be performed in parallel, sequentially, or in a different order, so long as the desired results of the technical solution of the present application are achieved, and the present application is not limited herein.
While the invention has been described with reference to a preferred embodiment, various modifications may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In particular, the technical features mentioned in the respective embodiments may be combined in any manner as long as there is no structural conflict. The present invention is not limited to the specific embodiments disclosed herein, but encompasses all technical solutions falling within the scope of the claims.
Claims (7)
1. A method of aerodynamic force determination, the method comprising:
After a target rigid segment model vibrates in a steady state, acquiring target images of the target rigid segment model at a plurality of wind speeds, wherein the target of the target rigid segment model comprises a first target circle, a second target circle and a cross mark, the cross mark is positioned 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 larger than that 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;
Obtaining 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 center of the second target circle, the pixel coordinates of the center of the first target circle and the conversion ratio of the preset pixel coordinates to the physical coordinates;
Determining a relative displacement time interval between a target rigid segment model under the current wind speed and a target rigid segment model under 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 circle center of the first target circle and the physical coordinates of the circle center of the second target circle;
Determining an inertial force and a damping force generated when the target rigid segment model vibrates, and determining a vertical component corresponding to the relative displacement time interval according to the relative displacement time interval and a conversion relation between preset displacement and force;
obtaining 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;
Before determining the relative displacement time course between the target rigid segment model and the target rigid segment model under the current 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 comprises:
Determining the diameter of the first target circle and the diameter of the second target circle according to the target image;
And determining the circle center position of the first target circle and the circle 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 of claim 1, wherein the determining inertial forces generated when the target rigid segment model vibrates comprises:
acquiring the total mass and the acceleration of the target rigid segment model during vibration;
and determining the inertial force generated when the target rigid segment model vibrates according to the total mass and the acceleration.
3. The method of claim 1, wherein determining a damping force generated when the target rigid segment model vibrates comprises:
acquiring the speed of a target rigid segment model when vibrating and the damping coefficient of the target rigid segment model;
and determining the damping force generated when the target rigid segment model vibrates according to the speed when the target rigid segment model vibrates and the damping coefficient.
4. The method of claim 1, wherein the target rigid segment mold further comprises a spring suspension system, a mold body, and two or more end plates;
The target is attached to the model body, and the center of the surface where the width and the height of the model body are located coincides with the center of the target;
The end plates are respectively nested at two ends of the model body, so that the model body is positioned between the two end plates;
The spring suspension system comprises a plurality of springs, wherein the lower ends of part of the springs are connected with the upper ends of the end plates, and the upper ends of part of the springs are connected with the lower ends of the end plates so as to suspend the end plates and the model body between the end plates.
5. A aerodynamic force determination device, the device comprising:
The system comprises an acquisition module, a target rigidity section model, a target acquisition module and a control module, wherein the acquisition module is used for acquiring target images of the target rigidity section model at a plurality of wind speeds after the target rigidity section model is in steady-state vibration, the target of the target rigidity section model comprises a first target circle, a second target circle and a cross mark, the cross mark is positioned 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 larger than the radius of the second target circle;
The displacement time interval determining module is used for determining the diameter of the first target circle and the diameter of the second target circle according to the target image; determining the circle center position of the first target circle and the circle center position of the second target circle according to the diameter of the first target circle and the diameter of the second target circle; determining 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 conversion ratio of 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 second target circle, the pixel coordinates of the diameter of the first target circle, the pixel coordinates of the center of the second target circle and the preset pixel coordinates to the physical coordinates, and obtaining the physical coordinates of the diameter of the first target circle, the physical coordinates of the center 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;
The component force determining module is used for determining an inertia force and a damping force generated when the target rigid segment model vibrates, and determining a vertical component force corresponding to the relative displacement time according to the relative displacement time and the conversion relation between the preset displacement and the force;
And the aerodynamic force determining module is used for obtaining aerodynamic force of the target rigid segment model according to the vertical component force, the inertia force and the damping force of the target rigid segment model.
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 the processor implements the aerodynamic force determination method according to any of claims 1-4 when executing the program.
7. A computer readable storage medium having stored thereon a computer program, characterized in that the program, when executed by a processor, implements the aerodynamic force determination method according to any of claims 1 to 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202510400532.2A CN119915477B (en) | 2025-04-01 | 2025-04-01 | Aerodynamic force determining method and device, electronic equipment and storage medium |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202510400532.2A CN119915477B (en) | 2025-04-01 | 2025-04-01 | Aerodynamic force determining method and device, electronic equipment and storage medium |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN119915477A CN119915477A (en) | 2025-05-02 |
| CN119915477B true CN119915477B (en) | 2025-07-11 |
Family
ID=95510977
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202510400532.2A Active CN119915477B (en) | 2025-04-01 | 2025-04-01 | Aerodynamic force determining method and device, electronic equipment and storage medium |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN119915477B (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104122066A (en) * | 2014-07-08 | 2014-10-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Synchronous measurement method of three-dimensional real-time attitude angle of low-speed wind tunnel test model |
| CN112949479A (en) * | 2021-03-01 | 2021-06-11 | 浙江大学 | Non-contact type rail sleeper relative displacement real-time measurement method based on deep learning and perspective transformation |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9171211B2 (en) * | 2013-09-20 | 2015-10-27 | Rapsodo Pte. Ltd. | Image processing for launch parameters measurement of objects in flight |
| CN109100112B (en) * | 2018-09-29 | 2020-01-17 | 浙江大学 | A computer vision-based testing method for plane wind vibration response of aeroelastic model wind tunnel test |
| CN117852336A (en) * | 2023-12-21 | 2024-04-09 | 天津大学 | Wind power plant full-coupling numerical simulation method and device, electronic equipment and storage medium |
-
2025
- 2025-04-01 CN CN202510400532.2A patent/CN119915477B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104122066A (en) * | 2014-07-08 | 2014-10-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Synchronous measurement method of three-dimensional real-time attitude angle of low-speed wind tunnel test model |
| CN112949479A (en) * | 2021-03-01 | 2021-06-11 | 浙江大学 | Non-contact type rail sleeper relative displacement real-time measurement method based on deep learning and perspective transformation |
Also Published As
| Publication number | Publication date |
|---|---|
| CN119915477A (en) | 2025-05-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| WO2022111423A1 (en) | Method for real-time identification, monitoring, and early warning of vortex-induced vibration event of long-span suspension bridge | |
| CN109596175B (en) | Wind power tower cylinder slope and rock on-line monitoring system | |
| CN111174961B (en) | A cable force optical measurement method and measurement system based on modal analysis | |
| Havaran et al. | Extracting structural dynamic properties utilizing close photogrammetry method | |
| CN114445404A (en) | Method and system for automatic identification of structural vibration response based on subpixel edge detection | |
| US20220113333A1 (en) | Method for calibrating linear vibration and angular vibration based on monocular vision | |
| CN114049559B (en) | Non-contact measurement method and device for overall dropper load of railway contact network | |
| US12163823B2 (en) | Weight estimation apparatus, weight estimation method, and computer-readable recording medium | |
| CN111397577A (en) | Tilt angle sensor and gyroscope fused tower monitoring system and method | |
| Zhao et al. | Distributed displacement response investigation technique for bridge structures using smartphones | |
| CN119915477B (en) | Aerodynamic force determining method and device, electronic equipment and storage medium | |
| CN108629085A (en) | A kind of girder structure Calculation Method of Deflection and apply its amount of deflection computing device | |
| CN119915479B (en) | Method and device for determining three-component force coefficient, electronic equipment and storage medium | |
| CN117272593B (en) | Wind tunnel test data analysis processing method | |
| CN113670572B (en) | A testing system and method for wind-driven rain load of building membrane structure | |
| CN103592093B (en) | Fire fighting truck boom tail end vibration measurement device, method and system and fire fighting truck | |
| CN110542430A (en) | A large dynamic performance testing device and method of an inertial measurement unit | |
| CN117073949A (en) | Performance evaluation device and method for transformer substation service steel framework | |
| CN115289952A (en) | Deformation quantity measurer, deformation quantity measuring method and device | |
| CN110457858B (en) | Method for determining modal vibration main shaft of high-rise building based on double-shaft actual measurement acceleration | |
| CN204329960U (en) | Based on the inclination angle dynamic measurement device of weight | |
| CN113654759A (en) | Aerodynamic testing system and method of building membrane structure under wind load | |
| CN120121199A (en) | Method, system, device and medium for real-time monitoring of cable tension of in-service cable bridge | |
| CN118129634B (en) | Steel structure deformation monitoring method and system | |
| CN120354043B (en) | A calculation method for the reasonable arch axis of through arch bridges |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |