Synchronous measurement system, method and equipment for conventional aerodynamic load and wake aerodynamic load of split conductor and storage medium

Abstract

The invention relates to a split conductor conventional aerodynamic load and wake aerodynamic load synchronous measurement system, method and device and a storage medium. The synchronous measurement system comprises a wind tunnel experiment section; the air blowing system is used for generating a stable incoming flow air field with an adjustable flow speed in the wind tunnel experiment section; the overall aerodynamic load measuring device is arranged in the wind tunnel experiment section in a replaceable manner; the sub-conductor aerodynamic load measuring device is arranged in the wind tunnel experiment section in a replaceable manner; the wake flow aerodynamic load measuring device is located at the downstream of the overall or sub-conductor aerodynamic load measuring device and is used for measuring a flow field structure of a wake flow area of the split conductor model in a non-contact manner; and the synchronous control unit is used for coordinating synchronous data acquisition of the overall aerodynamic load measuring device, the sub-conductor aerodynamic load measuring device, the wake flow aerodynamic load measuring device and the air blast system in time.

Description

Technical Field

[0001] This invention belongs to the field of wind tunnel experimental technology, specifically relating to a system, method, equipment, and storage medium for synchronous measurement of conventional aerodynamic loads and wake aerodynamic loads of a split conductor. Background Technology

[0002] Transmission lines are subjected to continuous aerodynamic excitation from natural wind fields during operation, leading to wind-induced vibration. The spatial distribution of aerodynamic loads on the lines directly determines their vibration response. Traditional aerodynamic load measurements primarily focus on the aerodynamic characteristics of a single line under uniform flow, including lift and drag coefficients, providing a reference for studying the overall aerodynamic behavior of the line. However, the wake effect of multi-segmented lines results in vibration characteristics of downstream lines with aerodynamic loads that are far more complex than in conventional cases. Accurately measuring the aerodynamic load distribution of the line in the wake region through wind tunnel experiments can reveal the excitation mechanism of line vibration under different flow field disturbances, providing crucial support for wind-induced vibration control and fatigue-resistant design.

[0003] Currently, wind tunnel experiments mostly use force balances to obtain the overall aerodynamic parameters of the conductor. However, research on the aerodynamic load distribution of each sub-conductor and the aerodynamic characteristics of the wake region within a split conductor is still relatively lacking, making it difficult to comprehensively reflect the true stress state and flow field evolution. The main reason for this situation is that simultaneously acquiring the aerodynamic loads of each sub-conductor and the wake region requires complex fixing and measuring devices. The aerodynamic loads of the sub-conductors are usually measured directly using a high-precision force balance, while the aerodynamic characteristics of the wake region require flow field visualization analysis using a particle image velocimetry (PIV) system. To simultaneously acquire two types of aerodynamic load data under the same experimental conditions, the force balance and the PIV system must operate in tandem, which places extremely high demands on the integration, synchronization, and stability of the experimental setup.

[0004] Therefore, there is an urgent need to develop a fixing method and a measurement method that can take into account both the overall aerodynamic load and the wake aerodynamic load, so as to provide key technical support for in-depth revelation of the flow field distribution law and the stress characteristics of the sub-conductors. Summary of the Invention

[0005] The purpose of this invention is to solve the problem of being unable to simultaneously acquire aerodynamic load data of the sub-lead and wake region under the same experimental conditions.

[0006] The objective of this invention is achieved through the following technical solution: This invention provides a system for simultaneously measuring conventional aerodynamic loads and wake aerodynamic loads of a split conductor, comprising: Wind tunnel test section; The blower system is connected to the inlet of the wind tunnel test section and is used to generate a stable and adjustable incoming airflow field in the wind tunnel test section. An overall aerodynamic load measuring device can be alternatively installed in the wind tunnel test section to measure the aerodynamic load on the split conductor as a whole in the wind field. A sub-conductor aerodynamic load measuring device can be alternatively installed in the wind tunnel test section for independently measuring the aerodynamic load of a single sub-conductor in a split conductor under turbulent conditions. The wake aerodynamic load measuring device is installed in the wind tunnel test section, located downstream of the overall aerodynamic load measuring device or the sub-lead aerodynamic load measuring device, and is used for non-contact measurement of the flow field structure in the wake region of the split lead model. The synchronization control unit is communicatively connected to the overall aerodynamic load measuring device, the sub-lead aerodynamic load measuring device, the wake aerodynamic load measuring device, and the blower system, respectively, and is used to coordinate the synchronous data acquisition of each system in time.

[0007] Furthermore, the overall aerodynamic load measuring device includes: A split conductor model, wherein the axis of the split conductor model is perpendicular to the incoming flow direction of the wind tunnel test section; At least two support end plates are arranged along the axial direction of the split conductor model; The force balance, with one end connected to the support end plate and the other end fixed to the wind tunnel wall of the wind tunnel test section, is used to support and measure the overall aerodynamic load of the split conductor model.

[0008] Furthermore, the support end plate is provided with multiple first balance mounting holes for mounting the force balance. A track is opened in the middle of the support end plate and multiple sets of first balance mounting holes are arranged. By adjusting the installation position of the force balance on the track, the initial angle of the split conductor model relative to the incoming wind can be changed conveniently and accurately to meet the testing requirements of different wind angles of attack.

[0009] Furthermore, the supporting end plate is made of carbon fiber. An integrated structure of "rigid end plate + high-frequency force balance" is adopted, with the end plate made of lightweight, high-rigidity material, balancing lightweight and high rigidity, to achieve real-time and accurate acquisition of the overall aerodynamic load (lift, drag, etc.) of the split conductor.

[0010] Furthermore, in the split conductor model, double-split and quadruple-split conductors are arranged according to the actual engineering spacing, while six-split and eight-split conductors are scaled down at a 1:2 ratio to ensure consistency between the model and the actual project.

[0011] Furthermore, the sub-conductor pneumatic load measuring device includes: A split conductor model, wherein the axis of the split conductor model is perpendicular to the incoming flow direction of the wind tunnel test section, and includes a target sub-conductor and multiple disturbance sub-conductors; A force balance is used to measure the aerodynamic load on the target sub-conductor. The force-measuring support plate has one target sub-guide mounting hole and two second-level balance mounting holes, which are used to connect the target sub-guide to the force-measuring balance, respectively. The spoiler support plate is provided with multiple sets of spoiler sub-wire mounting holes for fixing the other spoiler sub-wires except for the target sub-wire; The turbulence support plate is independent of the force measuring support plate.

[0012] The innovative design adopts a separate "force measuring support plate + turbulence support plate": the force measuring support plate connects only the target sub-conductor to the high-frequency force measuring balance and is used to independently measure the aerodynamic load of the target sub-conductor; the turbulence support plate is independent of the force measuring system, fixes the other turbulence sub-conductors, accurately reproduces the complex turbulence field between the split conductors in the real line, and ensures that the aerodynamic environment of the target sub-conductor is consistent with the actual project.

[0013] The force measuring support plate has only one target sub-lead mounting hole and two second-day horizontal mounting holes, making the structure simple; the turbulence support plate has multiple sets of turbulence sub-lead mounting holes centered on the sub-lead to be tested, according to different splitting spacing, wind attack angle and number of splits, to adapt to various split lead test scenarios.

[0014] Furthermore, the wake aerodynamic load measuring device is a particle image velocimetry system, comprising: A tracer particle generator is used to disperse tracer particles in the wake region of the wind tunnel test section. The light source excitation system includes a pulsed laser for generating pulsed laser light to illuminate the wake region to be measured; An image acquisition system, including a CCD camera and a controller synchronized with the pulsed laser, is used to acquire flow field images containing the tracer particles under the synchronous triggering of the pulsed laser. The data acquisition system is used to simultaneously acquire data from the particle image velocimetry system and the force balance. The data analysis system is used to process image data and calculate flow field parameters.

[0015] The PIV system does not have physical contact with the conductor model or force balance, thus avoiding interference with conventional aerodynamic load measurements, while it can be synchronized with the force measurement system.

[0016] Furthermore, the synchronization control unit is electrically connected to the blower system, laser system, image acquisition system, data acquisition system, and data analysis system, respectively.

[0017] Based on the same inventive concept, this invention also provides a method for simultaneously measuring the conventional aerodynamic load and wake aerodynamic load of a split conductor, comprising the following steps: In the wind tunnel test section, either the overall aerodynamic load measuring device or the sub-lead aerodynamic load measuring device is selectively installed. A stable and adjustable incoming airflow field is generated within the wind tunnel test section using a blower system. Under the influence of the incoming wind field, the installed aerodynamic load measuring device and the wake aerodynamic load measuring device are activated in a coordinated manner by the synchronous control unit to collect data in time synchronization. Specifically, when the overall aerodynamic load measuring device is installed, the overall aerodynamic load data of the split conductor model and its downstream wake flow field data are collected simultaneously; when the sub-conductor aerodynamic load measuring device is installed, the independent aerodynamic load data of the target sub-conductor and its downstream wake flow field data are collected simultaneously.

[0018] Furthermore, when selecting to install the overall pneumatic load measuring device, the specific steps include: The split conductor model is installed using at least two support end plates, ensuring that its axis is perpendicular to the incoming flow direction of the wind tunnel test section; A force balance is used to connect the support end plate to the wind tunnel wall to support the model and measure its overall aerodynamic load.

[0019] Furthermore, the force balance is installed by selecting mounting holes at different positions on the support end plate to adjust the initial angle of attack of the split conductor model relative to the incoming flow direction.

[0020] Furthermore, when selecting to install the sub-conductor pneumatic load measuring device, the specific steps include: Connect the target sub-guide wire to the force balance via the force support plate; The remaining spoiler conductors are mounted on an independently configured spoiler support plate; Ensure that the axis of all sub-guide wires is perpendicular to the incoming flow direction of the wind tunnel test section, and maintain a relative spatial position consistent with the actual engineering.

[0021] Furthermore, the data acquisition specifically includes: a force balance continuously recording five component force data, a particle image velocity measurement system simultaneously capturing particle motion images in the wake region, and a single working condition acquisition lasting 3-5 minutes to ensure data stability and sample size.

[0022] Furthermore, it also includes: repeatedly executing the method by changing at least one parameter among the following: wind speed of the blower system, wind angle of attack of the split conductor model, number of splits, spacing or diameter of sub-conductors, to achieve aerodynamic load testing under multiple operating conditions.

[0023] Compared with the prior art, the beneficial effects of the present invention are as follows: This invention provides a synchronous measurement system for conventional aerodynamic loads and wake aerodynamic loads of a split conductor, comprising: a wind tunnel test section; a blower system connected to the inlet of the wind tunnel test section for generating a stable and adjustable incoming wind field in the wind tunnel test section; an overall aerodynamic load measuring device, alternatively disposed within the wind tunnel test section, for measuring the aerodynamic loads experienced by the split conductor model as a whole in the wind field; a sub-conductor aerodynamic load measuring device, alternatively disposed within the wind tunnel test section, for independently measuring the aerodynamic loads of individual sub-conductors in the split conductor under turbulent conditions; a wake aerodynamic load measuring device, disposed within the wind tunnel test section and located downstream of the overall or sub-conductor aerodynamic load measuring device, for non-contact measurement of the flow field structure in the wake region of the split conductor model; and a synchronous control unit, communicatively connected to the overall aerodynamic load measuring device, the sub-conductor aerodynamic load measuring device, the wake aerodynamic load measuring device, and the blower system, for coordinating the synchronous data acquisition of each system over time. This invention achieves integrated measurement of conventional aerodynamic loads and wake aerodynamic loads, enabling precise revelation of their correspondence and improving the representativeness and applicability of the data. It provides an effective experimental method and means for in-depth research on the instantaneous coupling relationship between loads and flow fields, and for revealing the flow mechanism of aerodynamic interference in split conductors. The invention features a compact structure and direct measurement method, effectively avoiding the shortcomings of traditional methods that require multiple separate experiments, thus improving experimental efficiency and data integrity.

[0024] The present invention provides a method for simultaneously measuring conventional aerodynamic loads and wake aerodynamic loads of split conductors. First, the overall force data of the split conductor is obtained through an overall aerodynamic load measuring device. Then, the independent force data of a single target sub-conductor under turbulent conditions is obtained through a sub-conductor measuring device. The PIV system can be started simultaneously in both processes to achieve precise time-synchronous acquisition of "overall load / sub-conductor load-wake flow field", solving the problem that traditional methods cannot acquire two types of data at the same time. Attached Figure Description

[0025] Figure 1 This is a schematic diagram of the overall aerodynamic load measuring device arrangement of the present invention; Figure 2 This is a schematic diagram of the support end plate of the overall pneumatic load measuring device of the present invention; Figure 3 This is a schematic diagram of the arrangement of the sub-conductor pneumatic load measuring device of the present invention; Figure 4 This is a schematic diagram of the force-measuring support plate and the turbulence support plate of the sub-conductor aerodynamic load measuring device of the present invention; Figure 5 This is a flowchart of the preparation stage of the synchronous measurement method of the present invention; Figure 6This is a flowchart illustrating the operation and data acquisition of the synchronous measurement method of the present invention; Figure 7 This is a data processing flowchart of the synchronous measurement method of the present invention; Figure 8 This is an icing model of a crescent-shaped icing conductor according to Embodiment 3 of the present invention; Figures 9-14 The mean and root mean square values ​​of the aerodynamic force coefficients in Embodiment 3 of the present invention are given. Figure 9 and Figure 10 Different wind angles of attack c l The average and root mean square of the lift coefficient. Figure 11 and Figure 12 Different wind angles of attack c d The average and root mean square of the drag coefficient. Figure 13 and Figure 14 Different wind angles of attack c m The average value and root mean square of the torque coefficient; Figures 15-20 The instantaneous streamline diagrams and time-averaged streamline diagrams for three angles of attack—0°, 90°, and 180°—are shown in Embodiment 3 of the present invention. Figure 15 and Figure 16 The images show the instantaneous streamline diagram and the time-averaged streamline diagram at a wind angle of attack of 0°. Figure 17 and Figure 18 The images show the instantaneous streamline diagram and the time-averaged streamline diagram at a wind angle of attack of 90°, respectively. Figure 19 and Figure 20 The images show the instantaneous streamline diagram and the time-averaged streamline diagram at a wind angle of attack of 180°, respectively. Figure 21 This is a connection diagram of the electronic device in Embodiment 4 of the present invention; Among them, 100 is the wind tunnel test section; 110 is the wind tunnel wall; 200 is the blower system; 300 is the overall aerodynamic load measuring device; 310 is the split conductor model; 311 is the target sub-conductor; 312 is the turbulence sub-conductor; 320 is the support end plate; 321 is the conductor mounting hole; 322 is the first level mounting hole; 330 is the force balance; 400 is the sub-conductor aerodynamic load measuring device; 410 is the force support plate; 411 is the target sub-conductor mounting hole; 412 is the second level mounting hole; 420 is the turbulence support plate; 421 is the turbulence sub-conductor mounting hole; 422 is the support hanging hole; 500 is the wake aerodynamic load measuring device; 510 is the tracer particle generator; 520 is the laser system; 530 is the image acquisition system; 540 is the data acquisition system; 550 is the data analysis system; and 600 is the synchronization control unit. Detailed Implementation

[0026] The technical solutions in the embodiments of the present invention will be clearly and completely described below. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other instances that are improved or modified by those skilled in the art are within the scope of protection of the present invention. It should be understood that the embodiments of the present invention are only used to illustrate the technical effects of the present invention, and are not intended to limit the scope of protection of the present invention. Unless otherwise specified, the methods used in the embodiments are conventional methods.

[0027] Example 1 like Figures 1-4 As shown, this invention provides a split conductor aerodynamic load measurement system, which can accurately measure the overall aerodynamic load of a split conductor and the aerodynamic load of individual sub-conductors. It includes: a wind tunnel test section 100; a blower system 200 connected to the inlet of the wind tunnel test section 100 to generate a stable and adjustable inflow wind field in the wind tunnel test section 100; an overall aerodynamic load measuring device 300, alternatively disposed within the wind tunnel test section 100, for measuring the aerodynamic load on the split conductor as a whole in the wind field; and a sub-conductor aerodynamic load measuring device 400, alternatively disposed within the wind tunnel test section 100, for independently measuring the aerodynamic load of a single sub-conductor in a turbulent environment. Load; a wake aerodynamic load measuring device 500, installed in the wind tunnel test section 100 and located downstream of the overall aerodynamic load measuring device 300 or the sub-lead aerodynamic load measuring device 400, is used for non-contact measurement of the flow field structure in the wake region of the split lead wire; a synchronization control unit 600 is communicatively connected to the overall aerodynamic load measuring device 300, the sub-lead aerodynamic load measuring device 400, the wake aerodynamic load measuring device 500, and the blower system 200, respectively, and is used to coordinate the synchronous data acquisition of each system in time.

[0028] The overall aerodynamic load measuring device 300 includes: a split conductor model 310, the axis of which is perpendicular to the incoming flow direction of the wind tunnel test section 100; at least two support end plates 320 arranged along the axis of the split conductor model 100; and a force balance 330, one end of which is connected to the support end plate 310, and the other end of which is fixed to the wind tunnel wall 110 of the wind tunnel test section 100, for supporting and measuring the overall aerodynamic load of the split conductor model 310. In this embodiment, two support end plates 320 are used as an example, which are respectively installed at both ends of the wind tunnel test section 100 to fix the split conductor model 310 to be measured.

[0029] The core of this device is the use of a rigid support end plate to directly connect the split conductor model 310 to a high-frequency force balance 330. The high-frequency force balance 330 is a five-component balance, which serves both a supporting and measuring function. Therefore, the rigid support end plate is preferably made of carbon fiber, which balances light weight and high rigidity. The spacing between the split conductors in double-split and quadruple-split conductors is arranged according to actual engineering conditions, while the spacing in six-split and eight-split conductors is scaled down to a 1:2 ratio. Through this connection method, the force balance can accurately and in real-time collect the overall aerodynamic load acting on the entire split conductor model.

[0030] To facilitate convenient testing of the split conductor under different wind attack angles, the support end plate 320 is provided with multiple first balance mounting holes 322 for mounting the force balance. In this embodiment, a track is opened in the middle of the support end plate 320, and different conductor mounting holes 321 are arranged in the track. By selecting different positions of the first balance mounting holes 322 on the support end plate 320 to mount the force balance 330, the initial angle of the force balance 330 and the fixed split conductor model 310 relative to the incoming wind direction can be changed as a whole, thereby conveniently and accurately realizing the change of the wind attack angle of the split conductor. Figure 2 The diagram shown is a structural schematic of the support end plate 320 in this embodiment. The plate has 12 elliptical holes with an average angle interval of 30°, which can realize the overall aerodynamic load measurement under different wind attack angles of 0°, 30°, 60°, 90°, 120°, 150° and 180°. The center distance between the elliptical holes can be adjusted according to the connection method with the five-component balance, and the spacing of the wire mounting holes can be adjusted according to the wire split spacing.

[0031] like Figure 3 As shown, the sub-lead aerodynamic load measuring device 400 includes: a split lead wire model 310, the axis of which is perpendicular to the incoming flow direction of the wind tunnel test section 100, including a target sub-lead wire 311 and multiple turbulence sub-lead wires 322; a force balance 330 for measuring the aerodynamic load of the target sub-lead wire 311; a force support plate 410, having a target sub-lead wire connection hole 411 and multiple second-level balance mounting holes 412, for connecting the target sub-lead wire 311 to the force balance 330 respectively; and a turbulence support plate 420, having turbulence sub-lead wire mounting holes 421 for fixing the remaining turbulence sub-lead wires 312 except for the target sub-lead wire 311; the turbulence support plate 420 is independent of the force support plate 410.

[0032] like Figure 4As shown, the aerodynamic load support plate for the sub-lead in this embodiment comprises two parts. The central part is a force-measuring support plate 410, which is used to connect with the force-measuring balance 330 to measure the aerodynamic load of the sub-lead. The outer part is a turbulence support plate 420, which is used to install and fix the remaining turbulence sub-leads 312 other than the target sub-lead 311. The main purpose is to ensure the accuracy of experimental data and obtain the aerodynamic load of the target sub-lead 311 under the influence of the wake of other turbulence sub-leads 312. The turbulence support plate 420 is installed on the wind tunnel wall 110 through the support mounting holes 422. The turbulence support plate 420 and the wind tunnel wall 110 are connected by a track, which can adjust the angle to realize the aerodynamic load parameters of the sub-leads under different wind attack angles.

[0033] The sub-conductor aerodynamic load measuring device is used to independently measure the aerodynamic load on any target sub-conductor in a multi-split conductor configuration, while realistically simulating the aerodynamic interference effects of surrounding sub-conductors. The turbulence support plate is independent of the force balance system; its own aerodynamic load and that of the fixed turbulence sub-conductors are not collected by the force balance. However, the existence of these turbulence sub-conductors is crucial for accurately reproducing the complex turbulence field between split conductors in a real circuit. They ensure that the aerodynamic environment of the target sub-conductor is highly consistent with the actual situation, guaranteeing the authenticity and validity of the measurement results.

[0034] The turbulence support plate has multiple turbulence sub-wire mounting holes centered on the guide line to be measured, with different splitting intervals, different wind attack angles, and different splitting numbers, for connecting the turbulence sub-wires.

[0035] When measuring the aerodynamic load of a single sub-conductor, the target sub-conductor is mounted on a force-measuring support plate, while the remaining turbulence-causing sub-conductors are mounted on a turbulence-causing support plate. The relative spatial relationships between all sub-conductors are ensured to be completely consistent with the actual split conductor. Through this design that separates measurement from turbulence, this device ingeniously solves the technical challenge of accurately measuring the aerodynamics of a single component in a complex multi-body flow environment.

[0036] The wake aerodynamic load measurement device 500 aims to capture the fine flow field structure within the wake region of a multi-split conductor model and achieve synchronous linkage with a conventional aerodynamic load measurement system, thereby simultaneously acquiring the aerodynamic characteristics of the conductor and the flow field evolution process in the wake region. The wake aerodynamic load measurement device 500 is a particle image velocimetry system, comprising: a tracer particle generator 510 for dispersing tracer particles in the wake region of the wind tunnel experimental section; a laser system 520, including a pulsed laser for generating pulsed laser light to irradiate the wake region under test; an image acquisition system 530, including a CCD camera and a controller synchronized with the pulsed laser for acquiring flow field images containing the tracer particles under synchronous triggering of the pulsed laser; a data acquisition system 540 for synchronously acquiring data from the particle image velocimetry system and a force balance; and a data analysis system 550 for processing image data and calculating flow field parameters.

[0037] The wake aerodynamic load measurement device 500 is essentially a high-resolution image velocimetry (PIV) system that does not have any physical contact with the conductor model or force balance. The introduction of this device aims to reveal the generation and evolution of aerodynamic loads at the level of flow mechanism, further complementing force measurement devices and forming a comprehensive measurement system combining force and flow measurement, which can be verified through mathematical calculations.

[0038] The tracer particle generator 510 is used to uniformly and stably distribute micron-sized tracer particles in the wake section of the wind tunnel. These particles have good fluid tracking properties and can accurately reflect the instantaneous motion state of the air. The laser system 520 includes a pulsed laser for illuminating the wake region to be measured. The image acquisition system 530 includes a high-resolution CCD camera and a controller synchronized with the laser. The data analysis system 550 is a high-performance computer equipped with professional PIV image processing software and smooth analysis algorithms.

[0039] This system combines direct measurement using a high-frequency force balance with non-contact optical measurement using a PIV system to simultaneously acquire macroscopic aerodynamic loads and microscopic flow field structures of split conductors. The force balance measures conventional aerodynamic loads, including lift, drag, and torque coefficients. The introduction of the PIV system reveals complex physical mechanisms such as aerodynamic interference and wake vortex shedding, and acquires the wake field and vorticity field of the split conductor, providing an effective means for the study of wind-induced vibrations.

[0040] Example 2 like Figures 5-7 As shown, this embodiment provides a method for simultaneously measuring the conventional aerodynamic load and wake aerodynamic load of a split conductor. This method aims to achieve comprehensive and simultaneous measurement of the overall aerodynamic load, sub-conductor aerodynamic load, and wake aerodynamic load of the split conductor through a combination of experimental devices.

[0041] Includes the following steps: In the wind tunnel test section 100, either the overall aerodynamic load measuring device 300 or the sub-lead aerodynamic load measuring device 400 is selectively installed. Start the blower system 200 to generate a stable and adjustable incoming airflow field within the wind tunnel test section 100; Under the influence of the incoming wind field, the synchronous control unit 600 coordinates the activation of the installed aerodynamic load measuring device and the wake aerodynamic load measuring device 600 to perform time-synchronized data acquisition. Specifically, when the overall aerodynamic load measuring device 300 is installed, the overall aerodynamic load data of the split conductor and its downstream wake flow field data are collected simultaneously; when the sub-conductor aerodynamic load measuring device 400 is installed, the independent aerodynamic load data of the target sub-conductor and its downstream wake flow field data are collected simultaneously.

[0042] The overall aerodynamic load test includes: within the wind tunnel test section 100, a complete split conductor model 310 is directly mounted on a force balance 330 via a support end plate 320, allowing for adjustment of the wind attack angle. The wind tunnel is adjusted to the target wind speed and wind attack angle. After the flow field stabilizes, data from the monitoring balance is continuously collected to obtain information such as lift and drag experienced by the split conductor as a whole under this operating condition.

[0043] The aerodynamic load test of a single sub-conductor includes: replacing the measuring device with a dedicated support consisting of a force-measuring support plate 410 and a turbulence-disrupting support plate 420. The target sub-conductor 311 to be tested is independently mounted on the force-measuring support plate 410 of the force balance 310, while the remaining turbulence-disrupting sub-conductors 312 are fixed on the turbulence-disrupting support plate 420. The aerodynamic load on the target sub-conductor 311 itself under the aerodynamic interference of the surrounding turbulence-disrupting sub-conductors 312 is accurately obtained.

[0044] Simultaneously with any of the aforementioned load tests, a particle image velocimetry (PIV) system is deployed downstream of the conductor model, ensuring precise time synchronization between the PIV system's image acquisition of the wake velocity field and the load data from the force balance. This step yields the flow field structure precisely corresponding to the aerodynamic load, providing data support for revealing complex aerodynamic interference mechanisms.

[0045] The data acquisition specifically includes: a force balance continuously recording five component force data, a particle image velocity measurement system simultaneously capturing particle motion images in the wake region, and a single working condition acquisition lasting 3-5 minutes to ensure data stability and sample size.

[0046] The method for simultaneously measuring conventional aerodynamic loads and wake aerodynamic loads of split conductors includes the following operational steps: (1) Install the overall aerodynamic load measuring device for the split conductor according to the experimental requirements. Connect the split conductor model to the measuring end of the high-frequency force balance through a rigid end plate, and install it at the hole on the predetermined slide rail. If measuring a single sub-conductor, replace it with the aerodynamic load measuring device for the sub-conductor.

[0047] (2) According to the experimental plan, the initial wind attack angle of the split conductor model is set and fixed by the slide rail adjustment mechanism.

[0048] (3) Downstream of the split conductor model, set the measurement plane position of the PIV system according to the wake characteristics to be captured. Calibrate the light source generation system and the image acquisition system to ensure the accuracy of the velocity field calculation.

[0049] (4) Zero and calibrate the force balance. Start the particle generator and adjust the spray position and concentration until a flow field image with uniform particle distribution is obtained in the camera.

[0050] (6) Start the wind tunnel, adjust the wind speed according to the established experimental conditions, and stabilize it at the target value required for the experiment.

[0051] (7) Start the balance measuring device and the PIV system measuring device, and collect data. The force balance continuously records the experimental data of the five-component force. At the same time, the control laser of the PIV system works synchronously with the camera to continuously capture a series of images and record the instantaneous motion information of the tracer particles in the measurement plane. Each data acquisition lasts for 3 to 5 minutes to ensure the stability of data acquisition.

[0052] (8) Conventional aerodynamic load processing. The time series of the raw force signal collected by the force balance is preprocessed by digital filtering and detrending, and then statistical analysis is performed to obtain key aerodynamic parameters such as the total lift, drag, torque response and Strocha number of the system.

[0053] (9) Wake aerodynamic load processing. The images acquired by the PIV system are processed in batches to capture the trajectory of particles moving with the fluid and to calculate the two-dimensional instantaneous velocity field at each acquisition moment. Based on a large number of instantaneous velocity field samples, the average velocity field, vorticity field and other time-averaged statistical characteristics can be further calculated, and the vortex shedding frequency can be calculated, providing key basis for studying the aerodynamic interference of wake on conductors and the mechanism of wind-induced vibration.

[0054] (10) By changing parameters such as wind speed, wind angle of attack, spacing of split conductors and diameter of split conductors, the aerodynamic load influencing factors of split conductors can be studied.

[0055] Example 3 This embodiment provides a case study of simultaneous measurement of conventional aerodynamic load and wake aerodynamic load on a split conductor. The experiment uses the commonly used JL / G1A-400 / 35 steel-cored aluminum stranded wire as an example, with a conductor diameter of 26.8 mm. The experiment employed a single-split conductor with a crescent-shaped icing model attached, and the icing thickness was 0.75D (20 mm). The icing model at a specified wind angle of attack of 0° is as follows... Figure 8 As shown, the incoming wind direction is from left to right, and the wind speed is uniformly distributed vertically. To accurately simulate the variation of aerodynamic coefficients with wind angle of attack and considering the axisymmetry of the icing conductor model, the wind angle of attack in the calculation case gradually increases to 180° in clockwise intervals of 5°. Since the wind speed of icing conductor galloping in actual engineering is generally 8~14 m / s, the incoming wind speed in this experiment was taken as 12 m / s, and the turbulence intensity was taken as 5%. The experimental curves are shown below. Figures 9-14 As shown. The five-component balance measures resistance. F D =50kgf, lift F L =120kgf, pitching moment M Z =12kgf·m, accuracy: 0.03%.

[0056] In the experiment, PIV was performed using a side-view measurement method. To avoid the adverse effects of light reflection on the original particle images, the back of the iced conductor segment model and the wind tunnel test section were uniformly painted with matte black paint. The high-speed camera used in the experiment had a sampling frequency of 1000Hz, with a single frame image exposure time of 5μs to 49d, and 400 images were acquired each time. To fully capture the flow field in the wake region of the iced conductor, the model was placed at 1 / 4 of the high-speed camera's field of view. The particle images obtained in the experiment had a resolution of 1600×1200 pixels. When processing the cross-correlation coefficients of the original particle images, a query window of 32×32 pixels was selected, and the iteration window coefficient was 50%, ultimately resulting in a velocity field with 99×74 velocity vectors in a two-dimensional plane. The instantaneous streamline diagrams and time-averaged streamline diagrams of the conductor under icing conditions at three angles of attack (0°, 90°, and 180°) obtained through the PIV experiment are shown below. Figures 10-20 As shown, X and Y are the flow direction coordinates and vertical coordinates of the model in the wind tunnel, respectively.

[0057] Figures 9-14The curves showing the aerodynamic coefficients of a crescent-shaped icing conductor under a wind speed of 12 m / s as a function of wind angle of attack reveal that the overall characteristics of the aerodynamic coefficients remain consistent at this wind speed. Both the lift and torque coefficients exhibit abrupt jumps in the 140°–160° range. The lift coefficient changes approximately antisymmetric about 90°, while the drag coefficient changes approximately symmetrical about 90°. The absolute values ​​of the lift, drag, and torque coefficients do not reach their maximum values ​​simultaneously. The lift coefficient reaches its maximum value near 50° and 120°, the drag coefficient near 80°, and the torque coefficient near 120°. At wind angles of attack of 0° and 180°, the absolute values ​​of the lift, drag, and torque coefficients are almost zero, and their root mean square values ​​are also very small. Between wind angles of attack of 50° and 130°, the lift coefficient changes almost linearly, while the drag and torque coefficients remain essentially at their maximum values. When the angle of attack of an icing conductor approaches 90°, the root mean square value of the aerodynamic coefficient will increase.

[0058] from Figures 15-20 As can be seen, at a wind angle of attack of 0°, there is virtually no flow separation on the icy guide wall; the boundary layer remains laminar and symmetrical, and no alternating vortices form in the wake region. At a wind angle of attack of 180°, significant flow separation occurs on the icy guide wall. The upstream boundary layer remains laminar, but after a certain distance past the highest and lowest points of the guide, flow separation occurs, and the boundary layer transitions from laminar to turbulent, forming alternating vortices in the wake region. However, the time-averaged flow field exhibits significant symmetry. At a wind angle of attack of 90°, flow separation occurs at the guide apex and the icing tip. The boundary layer rapidly transitions from laminar to turbulent, forming alternating vortices in the wake region. The turbulent integral scale of the vortices formed after separation at the guide apex is larger than that of the vortices formed after separation at the icing tip, exhibiting significant asymmetry.

[0059] In summary, the proposed system and method for synchronously measuring the aerodynamic characteristics and wake field of a split conductor, through a combination of direct measurement using a high-frequency force balance and non-contact optical measurement using a PIV system, achieves simultaneous acquisition of macroscopic aerodynamic loads and microscopic flow field structures of the split conductor. The force balance enables the measurement of conventional aerodynamic loads, including coefficients for lift, drag, and torque. The introduction of the PIV system reveals complex physical mechanisms of aerodynamic interference and wake vortex shedding, and acquires the wake field and vorticity field of the split conductor, providing an effective means for the study of wind-induced vibrations. This invention features a compact structure and direct measurement method, effectively avoiding the need for multiple separate experiments in traditional methods, thus improving experimental efficiency and data integrity. Simultaneously, the integrated measurement of conventional aerodynamic loads and wake aerodynamic loads allows for precise revelation of their correspondence, enhancing the representativeness and applicability of the data. This provides an effective experimental method and means for in-depth research on the instantaneous coupling relationship between loads and flow fields, and for revealing the flow mechanism of aerodynamic interference in split conductors.

[0060] Example 4 like Figure 21 As shown, the present invention also provides an electronic device, which may be a computer device, a microcontroller device, a smart mobile device, etc. The electronic device in this embodiment may include a processor, a memory, a transceiver component, etc. The memory, processor, and transceiver component are connected via a bus; the memory can be used to store executable programs, and an exemplary executable program may include instructions; the processor is used to execute the instructions stored in the memory. The memory can also be used to store data, which can be accessed and / or modified when instructions are executed.

[0061] The processor may be a Central Processing Unit (CPU), or it may be other general-purpose processors, digital signal processors (DSPs), application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. It is the computing and control core of the terminal, and it is suitable for implementing one or more instructions. Specifically, it is suitable for loading and executing one or more instructions in the storage medium to realize the corresponding method flow or corresponding function, so as to realize the steps of the method for synchronous measurement of conventional aerodynamic load and wake aerodynamic load of a split conductor in the above embodiment.

[0062] Example 5 Based on the same inventive concept, this invention also provides a readable storage medium, specifically an electronic device readable storage medium (Memory). This readable storage medium is a memory device within an electronic device used to store programs and data. It is understood that the storage medium here can include both built-in storage media within the electronic device and extended storage media supported by the electronic device. The storage medium provides storage space, which stores the terminal's operating system. Furthermore, this storage space also stores one or more instructions suitable for loading and execution by a processor. These instructions can be one or more executable programs (including program code). It should be noted that the storage medium here can be a high-speed RAM memory or a non-volatile memory, such as at least one disk storage device. Loading and executing one or more instructions stored in the storage medium by the processor can implement the steps of the method for synchronously measuring conventional aerodynamic loads and wake aerodynamic loads of a split-wire in the above embodiments.

[0063] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A system for synchronously measuring conventional aerodynamic loads and wake aerodynamic loads of a split conductor, characterized in that, include: Wind tunnel test section; The blower system is connected to the inlet of the wind tunnel test section and is used to generate a stable and adjustable incoming airflow field in the wind tunnel test section. An overall aerodynamic load measuring device can be alternatively installed in the wind tunnel test section to measure the aerodynamic load on the split conductor as a whole in the wind field. A sub-conductor aerodynamic load measuring device can be alternatively installed in the wind tunnel test section for independently measuring the aerodynamic load of a single sub-conductor in a split conductor under turbulent conditions. The wake aerodynamic load measuring device is installed in the wind tunnel test section and located downstream of the overall aerodynamic load measuring device or the sub-lead aerodynamic load measuring device. It is used for non-contact measurement of the flow field structure in the wake region of the split lead model. The synchronization control unit is communicatively connected to the overall aerodynamic load measuring device, the sub-lead aerodynamic load measuring device, the wake aerodynamic load measuring device, and the blower system, respectively, and is used to coordinate the synchronous data acquisition of each system in time.

2. The system according to claim 1, characterized in that, The overall aerodynamic load measuring device includes: A split conductor model, wherein the axis of the split conductor model is perpendicular to the incoming flow direction of the wind tunnel test section; At least two support end plates are arranged along the axial direction of the split conductor model; The force balance, with one end connected to the support end plate and the other end fixed to the wind tunnel wall of the wind tunnel test section, is used to support and measure the overall aerodynamic load of the split conductor model.

3. The system according to claim 2, characterized in that, The support end plate is provided with a plurality of first balance mounting holes for installing the force measuring balance.

4. The system according to claim 2, characterized in that, The support end plate is made of carbon fiber.

5. The system according to claim 2, characterized in that, In the split conductor model, double-split and quadruple-split conductors are arranged according to the actual engineering spacing, while six-split and eight-split conductors are scaled down at a 1:2 ratio.

6. The system according to claim 1, characterized in that, The sub-conductor aerodynamic load measuring device includes: A split conductor model, wherein the axis of the split conductor model is perpendicular to the incoming flow direction of the wind tunnel test section, and includes a target sub-conductor and multiple disturbance sub-conductors; A force balance is used to measure the aerodynamic load on the target sub-conductor. The force-measuring support plate has one target sub-guide mounting hole and two second-level balance mounting holes, which are used to connect the target sub-guide to the force-measuring balance, respectively. The spoiler support plate is provided with multiple sets of spoiler sub-wire mounting holes for fixing the other spoiler sub-wires except for the target sub-wire; The turbulence support plate is independent of the force measuring support plate.

7. The system according to claim 1, characterized in that, The wake aerodynamic load measuring device is a particle image velocimetry system, comprising: A tracer particle generator is used to disperse tracer particles in the wake region of the wind tunnel test section. The light source excitation system includes a pulsed laser for generating pulsed laser light to illuminate the wake region to be measured; An image acquisition system, including a CCD camera and a controller synchronized with the pulsed laser, is used to acquire flow field images containing the tracer particles under the synchronous triggering of the pulsed laser. The data acquisition system is used to simultaneously acquire data from the particle image velocimetry system and the force balance. The data analysis system is used to process image data and calculate flow field parameters.

8. The system according to claim 1, characterized in that, The synchronization control unit is electrically connected to the blower system, laser system, image acquisition system, data acquisition system, and data analysis system, respectively.

9. A method for simultaneously measuring conventional aerodynamic load and wake aerodynamic load of a split conductor, characterized in that, Includes the following steps: In the wind tunnel test section, the overall aerodynamic load measuring device or the sub-lead aerodynamic load measuring device is selected and installed based on the measurement scheme. A stable and adjustable incoming airflow field is generated within the wind tunnel test section using a blower system. Under the influence of the incoming wind field, the installed aerodynamic load measuring device and the wake aerodynamic load measuring device are activated in a coordinated manner by the synchronous control unit to collect data in time synchronization. Specifically, when the overall aerodynamic load measuring device is installed, the overall aerodynamic load data of the split conductor model and its downstream wake flow field data are collected simultaneously; when the sub-conductor aerodynamic load measuring device is installed, the independent aerodynamic load data of the target sub-conductor and its downstream wake flow field data are collected simultaneously.

10. The method according to claim 9, characterized in that, When selecting to install the overall pneumatic load measuring device, the specific steps include: The split conductor model is installed using at least two support end plates, ensuring that its axis is perpendicular to the incoming flow direction of the wind tunnel test section; A force balance is used to connect the support end plate to the wind tunnel wall to support the model and measure its overall aerodynamic load.

11. The method according to claim 10, characterized in that, The force balance is installed by selecting mounting holes at different positions on the support end plate to adjust the initial angle of attack of the split conductor model relative to the incoming flow direction.

12. The method according to claim 10, characterized in that, When selecting to install the sub-conductor pneumatic load measuring device, the specific steps include: Connect the target sub-guide wire to the force balance via the force support plate; The remaining spoiler conductors are mounted on an independently configured spoiler support plate; Ensure that the axis of all sub-guide wires is perpendicular to the incoming flow direction of the wind tunnel test section, and maintain a relative spatial position consistent with the actual engineering.

13. The method according to claim 9, characterized in that, Also includes: By changing at least one parameter among the following: wind speed of the blower system, wind angle of attack of the split conductor model, number of splits, spacing or diameter of sub-conductors, the method can be repeatedly executed to achieve aerodynamic load testing under multiple operating conditions.

14. The method according to claim 9, characterized in that, The data acquisition specifically includes: a force balance continuously recording five component force data, a particle image velocity measurement system simultaneously capturing particle motion images in the wake region, and a single working condition acquisition lasting 3-5 minutes.

15. An electronic device, characterized in that, include: At least one processor and memory; The memory and processor are connected via a bus; The memory is used to store one or more programs; When the one or more programs are executed by the at least one processor, the method for synchronous measurement of conventional aerodynamic load and wake aerodynamic load of split conductors as described in any one of claims 9 to 14 is implemented.

16. A readable storage medium, characterized in that, It contains an execution program, which, when executed, implements the method for synchronous measurement of conventional aerodynamic load and wake aerodynamic load of split conductors as described in any one of claims 9 to 14.

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