Method and device for testing strength characteristics of wings of fixed-wing unmanned aerial vehicle under mechanical stress

Abstract

The invention relates to the technical field of fixed-wing unmanned aerial vehicle manufacturing quality detection, and provides a method and a device for testing strength characteristics of wings of a fixed-wing unmanned aerial vehicle under mechanical stress, the device comprises a grid frame provided with a plurality of vertical through holes, an air bag system is arranged around the through holes, and deformation measurement composition rods with mark points at the top ends are arranged in the through holes in a penetrating manner. A foldable supporting ring is arranged on the edge of the bottom of the grid frame, and a flexible conductive fiber network made of a graphene / silver nanowire composite material is arranged on the supporting ring and used for precise measurement of a wing root area. The test method comprises the following steps: fixing a to-be-tested wing on the support frame body; carrying out graded loading on the wing, obtaining wing body area deformation data through a deformation measurement composition rod, and obtaining wing root area deformation data through a conductive fiber network; performing fusion processing on the angle data, the displacement value and the three-dimensional deformation data; and measuring the wing on the other side by adopting the same parameters, and performing symmetry matching screening.

Description

Technical Field

[0001] The present invention relates to the technical field of fixed-wing UAV manufacturing quality inspection, and in particular to a method and device for testing the strength characteristics of a fixed-wing UAV wing under mechanical stress. Background Art

[0002] Fixed-wing UAVs are important aircraft, and the performance of their wings directly affects flight safety and stability. In actual production, due to differences in manufacturing processes and material properties, even wings produced in the same batch may have different strength characteristics. Especially for left-right symmetrical wings, if the strength characteristics of the wings on both sides are inconsistent, it will lead to asymmetric deformation during flight, affecting flight performance.

[0003] At present, the measurement of wing strength characteristics is mainly carried out through static loading test, setting several measurement points on the wing surface, and using displacement sensors to measure the deformation under different loads. This method is simple to operate, but the measurement points are limited and it is difficult to fully reflect the deformation characteristics of the wing. At present, some wing strength detection devices have been developed and used. For example, the Chinese utility model patent with patent number CN 219890958 U discloses a wing compression detection device for UAV production, which includes a frame, a lower clamping plate, an upper clamping plate and a rotating rod mechanism. By setting a fixed lower clamping plate on the inner wall of the frame and driving the upper clamping plate through a rotating rod threaded at the upper end of the frame, the wing can be clamped and detected. Although the device can complete the basic compression detection function, it still has the following shortcomings: 1. The measurement method is single and can only perform simple compressive strength tests, but cannot obtain the comprehensive deformation characteristics of the wing under actual stress conditions; 2. The device has a simple structure and lacks accurate means of measuring the deformation of the wing surface, making it difficult to achieve matching and screening of the left and right wings; 3. The measurement process requires a lot of manual operation, which is inefficient and the repeatability of the measurement results is poor. Summary of the invention

[0004] The purpose of the present invention is to solve the shortcomings of the prior art. The present invention provides a method and device for measuring the wing strength characteristics of a fixed-wing UAV that integrates a rigid measurement component and a flexible conductive network. Through the coordinated measurement of the wing body and wing root area, accurate measurement and optimal symmetrical matching of the wing strength characteristics are achieved.

[0005] In order to solve the above problems, the present invention adopts the following scheme: a method for measuring and symmetric matching the wing strength characteristics of a fixed-wing UAV, using a measuring device including a support frame, a graded stress generating counterweight module, an XY-axis measurement platform positioning mechanism and a wing-body partition deformation measurement component, wherein: the wing-body partition deformation measurement component includes a lattice frame provided with a plurality of vertical through holes, an airbag system arranged around the vertical through holes, and a deformation measurement component rod penetrating the vertical through holes, and a marking point is provided at the top of the deformation measurement component rod; the method comprises the following steps: S1. System initialization and wing installation: Checking the air tightness of the airbag system, the reset state of the deformation measurement component rod, and the working state of the camera device; The wing to be tested is fixedly mounted on the mounting seat of the support frame; S2. Multi-dimensional measurement data collection: Divide the wing surface into multiple measurement areas from the wing handle to the wing tip; The wing is loaded in stages by the graded stress generating counterweight module. Under each load stage: Collect angle change data of each measurement area through an angle sensor; Collect the displacement value of the wing tip; Controlling the airbag system so that the deformation measurement component rod array contacts the wing surface in sequence; Acquire the spatial position data of the marking point at the top end of the deformation measurement component rod by the camera device; S3. Data processing and strength characteristics analysis: Perform fusion processing on the collected angle data, displacement value and three-dimensional deformation data; Reconstruct the three-dimensional deformed surface of the wing surface; Calculate the stiffness characteristics and strength distribution of the wing under different loads; S4, symmetry matching screening: The same measurement parameters and process are used to measure the symmetrical wing on the other side; Calculate the angle difference, displacement difference and deformation difference of the corresponding measuring points on both sides of the wings; Establish a comprehensive scoring mechanism that includes strength property consistency and deformation symmetry; The best matching wing combination is selected based on the comprehensive scoring results.

[0006] The beneficial effects of this technical solution are as follows: through the collection and fusion processing of multi-dimensional measurement data, combined with angle, displacement and three-dimensional deformation data, a comprehensive measurement of the wing strength characteristics is achieved, and through a systematic symmetry matching screening method, the optimal matching of the left and right wings is ensured.

[0007] Preferably, the XY measurement platform positioning mechanism includes: an X-direction moving structure, including a horizontal X-direction guide rail arranged on the support frame, a slider slidably connected to the horizontal X-direction guide rail, and a crossbeam frame fixed on the slider; a Y-direction moving structure, including a horizontal Y-direction guide rail fixed on the crossbeam frame and perpendicular to the horizontal X-direction guide rail, and a moving seat slidably connected to the horizontal Y-direction guide rail; the wing-body partition deformation measurement component is connected to the moving seat. The beneficial effects of this technical solution: a stable and reliable two-dimensional moving platform is provided, ensuring that the measurement component can be accurately positioned at each measurement area of ​​the wing, and improving the accuracy and efficiency of the measurement.

[0008] Preferably, the wing-body partition deformation measurement assembly further includes: a height adjustment structure for adjusting the height position of the lattice frame; the side wall of the lattice frame is provided with an air inlet and an air outlet connected to the airbag system, and the air inlet and the air outlet are both provided with a one-way valve. The beneficial effect of this technical solution: through the height adjustment structure and the airtight control system, the precise positioning and reliable air pressure control of the measurement assembly are achieved, and the stability of the measurement process is ensured.

[0009] Preferably, dividing the measurement area in step S2 includes: determining the position of key measurement points according to the structural characteristics of the wing; increasing the density of measurement points in the area where the airfoil changes greatly; and marking the measurement reference at each determined measurement point. Through a reasonable measurement point layout strategy, especially by encrypting measurement points in key areas, the measurement accuracy of important areas is improved and more representative data is obtained.

[0010] Preferably, the hierarchical loading in step S2 includes: formulating a hierarchical loading scheme including load level, loading time, and stabilization time; applying load step by step according to preset loading levels; maintaining a predetermined stabilization time after each level of load application is completed; and real-time monitoring and recording of each level of load value and load stability. The beneficial effects of this technical solution: through a systematic hierarchical loading scheme and real-time monitoring mechanism, the stability and controllability of load application are ensured, and the reliability of measurement data is improved.

[0011] Preferably, after completing the measurement of a measurement area, the deformation measurement component rod is reset to the initial state by the retracting plate, and the XY measurement platform positioning mechanism is controlled to move to the next measurement area. The beneficial effect of this technical solution: through the design of the retracting plate, the deformation measurement component rod is reliably reset, ensuring the stability and efficiency of the continuous measurement process.

[0012] Preferably, the data fusion processing in step S3 includes: removing outliers from the collected angle data, displacement values ​​and three-dimensional deformation data; processing the measurement data using a data smoothing algorithm; and integrating the angle data, displacement values ​​and three-dimensional deformation data using a multi-source data fusion algorithm. The beneficial effects of this technical solution are: through a multi-level data processing method, outliers are effectively removed, data quality is improved, and effective fusion of multi-source data is achieved.

[0013] Preferably, the comprehensive scoring mechanism in step S4 includes: calculating the difference in stiffness characteristics of the two wings at various levels of load; analyzing the deformation symmetry deviation of the two wings; evaluating the strength distribution consistency of the two wings; and calculating the comprehensive matching score according to the preset weight. The beneficial effects of this technical solution: a comprehensive scoring mechanism is established, and the scientificity and accuracy of the left and right wing matching screening are ensured through matching evaluation in multiple dimensions.

[0014] The present invention also provides a device for measuring the wing strength characteristics of a fixed-wing unmanned aerial vehicle, comprising: a support frame, on which a mounting seat for mounting the wing is provided; a graded stress generating counterweight module, for applying a controllable test load on the wing; an angle measuring device, for collecting angle data of wing deformation; a displacement measuring device, for measuring the deformation of the wing tip; an XY-direction measurement platform positioning mechanism, comprising: an X-direction moving structure, comprising a horizontal X-direction guide rail arranged on the support frame, a slider slidably connected to the horizontal X-direction guide rail, a driving motor for driving the slider to move on the horizontal X-direction guide rail, and a crossbeam frame fixed on the slider; a Y-direction moving structure, comprising a horizontal X-direction guide rail fixed on the crossbeam frame and perpendicular to the horizontal X-direction guide rail. A Y-guide rail, a movable seat slidably connected to the horizontal Y-guide rail, and a driving device for driving the movable seat to move on the horizontal Y-guide rail; a wing-body partition deformation measurement component, connected to the movable seat, including: a lattice frame, in which a plurality of vertical through holes distributed in a matrix are provided; an airbag system, arranged around the vertical through holes, for controlling the lifting and lowering of the deformation measurement component rod; a plurality of deformation measurement component rods, respectively inserted into the vertical through holes, with marking points for spatial position tracking at the top thereof; a height adjustment structure, for adjusting the height position of the lattice frame; a high-definition camera device, for real-time recording of the spatial position information of the marking points; a processor, for fusing angle data, displacement data and three-dimensional deformation data. The beneficial effects of this technical solution: an integrated measurement device is provided, which realizes high-precision measurement of wing strength characteristics through the coordinated work of multiple measurement methods.

[0015] Preferably, it also includes a return plate arranged on the support frame, which is used to reset the deformation measurement component rod to an initial state. The beneficial effect of this technical solution is that through a special reset mechanism, it is ensured that the measurement component can reliably return to the initial state, thereby improving the repeatability and work efficiency of the measurement. Compared with the prior art, the technical solution of the present invention has the following advantages: The present invention realizes high-precision measurement and optimal symmetric matching of the wing strength characteristics of a fixed-wing UAV through an innovative method and device.

[0016] The design combines the deformation measurement component rod with the airbag system, and cooperates with the XY measurement platform positioning mechanism, so that the measurement device can accurately locate and obtain the deformation data of the wing surface. Especially for the key part of the wing-the wing root area, an innovative conductive fiber network measurement system is set at the bottom of the lattice frame. Through the highly sensitive flexible conductive fiber and dense sensor network layout, it can accurately capture the tiny deformation of the wing root area. At the same time, the angle measurement and displacement measurement functions are integrated to realize the collection of multi-dimensional data. During the measurement process, the graded stress generation counterweight module provides a stable and controllable load, and the retracting plate ensures the reliable resetting of the deformation measurement component rod, making the entire measurement process efficient and repeatable.

[0017] In terms of data processing, the reliability of the measurement data is improved through outlier elimination, data smoothing and multi-source data fusion algorithms. For the matching and screening of the left and right wings, an evaluation system including stiffness characteristics, deformation symmetry and strength distribution was established, combined with the precise deformation data of the wing root area to ensure the accuracy of the matching results.

[0018] The entire measurement process is highly automated, easy to operate, and the measurement results are intuitive and reliable, providing strong technical support for improving the manufacturing quality of UAVs. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the figures required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the figures described below are only some embodiments of the present application. For ordinary technicians in this field, other figures can be obtained based on these figures without paying creative work.

[0020] Figure 1 It is a schematic diagram of the structure of the wings on both sides of the fixed-wing UAV in the present invention; Figure 2 is a schematic diagram of measuring the bending angle of the wing loading position in the present invention; Figure 3 This is a flowchart of the working process of Embodiment 1 of the present invention; Figure 4 It is a partial structural schematic diagram of the present invention; Figure 5 It is a partial structural schematic diagram of another angle of the present invention; Figure 6 It is a schematic diagram of the overall structure of the present invention; Figure 7 It is a partial structural schematic diagram of another angle of the present invention; Figure 8 It is a structural schematic diagram of the conductive fiber network measurement system of the present invention; Fig. 9 It is a schematic diagram of measuring the curved surface of the wing in different regions in the present invention.

[0021] Reference numerals: Wing 02, wing handle 021, mounting seat 03, support frame 10, graded stress generating counterweight module 20, XY measurement platform positioning mechanism 30, X-direction moving structure 31, horizontal X-direction guide rail 311, slider 312, drive motor 313, crossbeam frame 314, Y-direction moving structure 32, horizontal Y-direction guide rail 321, moving seat 322, wingtip height measuring ruler 40, wing-body partition deformation measurement assembly 50, lattice frame 51, deformation measurement component rod 52, air inlet 53, air outlet 54, height adjustment structure 55, support ring 60, conductive fiber network 61, conductive fiber 611, retraction plate 80. DETAILED DESCRIPTION

[0022] The following will be combined Figure 1-Figure 9 The preferred embodiments of the present invention are described in detail. It should be noted that the following description is only a preferred embodiment of the present invention, rather than a limitation of the present invention. Those skilled in the art should understand that various modifications and variations can be made to the present invention without departing from the spirit and scope of the present invention. The scope of protection of the present invention shall be subject to the attached claims.

[0023] Example 1: Basic measurement and matching screening method This embodiment provides a basic measurement and matching screening method for the strength characteristics of a fixed-wing UAV wing. The method is used to detect the characteristic changes of the material surface shape (such as curvature, stiffness and strength) in the segmented area of ​​wing 02 (wing 02 refers to the mutually symmetrical left wing or right wing) under the same mechanical stress. The method includes the following steps: 1. Wing installation and measurement preparation 1.1 Wing 02 fixing steps: (1) Pretreatment of Wing 02: Check the appearance of Wing 02 to ensure there are no obvious defects; clean the surface of Wing 02 to remove impurities that may affect the measurement; mark reference points in the predetermined measurement area.

[0024] (2) Positioning of wing 02: Select a suitable fixing point on the wing handle 021 according to the structural characteristics of wing 02; ensure that the fixing point does not affect the natural deformation of wing 02; ensure that the left and right wings use the same positioning method; and confirm that the fixing device does not interfere with the measurement.

[0025] 1.2 Measurement system initialization: Before the measurement begins, first check the measurement environment to ensure that the ambient temperature and humidity are within the standard range, that there is no vibration or strong electromagnetic interference at the measurement site, and that the lighting conditions are appropriate. Establish the coordinate origin based on the fixed end of wing 02 to determine the reference position and boundary range of the measurement area. Calibrate all measurement sensors, including zero point calibration of the displacement measurement system, accuracy verification of the angle measurement system, and metrological inspection of the load application device.

[0026] 2. Measurement point arrangement and stress loading 2.1 Determination of measuring points: To ensure the accuracy and representativeness of the measurement results, the measurement area is first divided on the surface of wing 02, and the key measurement points are determined from the wing handle 021 to the wing tip according to the structural characteristics of wing 02. The arrangement of the measurement points needs to take into account the change law of the airfoil, and the measurement points should be appropriately encrypted in areas where the airfoil changes greatly. For the left and right wings 02, the positions of the measurement points must be strictly corresponding to ensure the accuracy of the subsequent symmetry comparison. The measurement benchmark is marked at each determined measurement point. The measurement benchmark should include displacement measurement points, angle measurement points, and stress application points, and the benchmark mark must not affect the deformation characteristics of wing 02.

[0027] 2.2 Hierarchical loading process: According to the structural characteristics and strength requirements of wing 02, a graded loading plan is formulated. At each measuring point, the load is gradually applied according to the preset loading level, and the loading process of each level of load should be kept uniform and stable. During the load application process, the deformation of wing 02 needs to be observed in real time to ensure that the deformation of wing 02 under each level of load is within the preset range. After each level of load is applied, a certain stabilization time is maintained, and relevant data is collected after the deformation of wing 02 is stabilized. During the entire loading process, the load values ​​at each level should be recorded synchronously, and the direction of the load should be monitored to ensure that the load is always perpendicular to the surface of wing 02.

[0028] 3. Data collection process (see Figure 2 and Figure 3 ) 3.1 Angle data collection: Under the action of various levels of load, a systematic angle measurement method is used to collect angle change data of each measuring point of wing 02 in the order from wing handle to wing tip. Figure 2As shown, the wing 02 is divided into three characteristic areas L1, L2, and L3 along the span direction, and multiple measurement points are set in each area to form a measurement network distributed in sequence from the wing handle 021 to the wing tip. The angle sensor collects angle sequence data such as ∠A, ∠B, ∠C at each measurement point. This continuous angle change sequence not only reflects the bending deformation degree of the wing 02 at different positions, but also reflects the gradual and continuous characteristics of the deformation.

[0029] To ensure the measurement accuracy, repeated measurements are used at the measurement points in each area. The statistical average is obtained through multiple acquisitions to effectively reduce the impact of random errors. At the same time, the system also records the angle increment relationship between adjacent measurement points. This relative angle change measurement method can accurately reflect the local characteristics of the deformation of wing 02. During the data acquisition process, the load sensor monitors and records the size of the applied load in real time to ensure that the load remains stable during the angle measurement.

[0030] An important feature of the measurement system is the establishment of a complete angle-load response curve. In each measurement area, the system records the angle changes under different load levels. By analyzing these response curves, the stiffness distribution characteristics of Wing 02 can be evaluated. In particular, after completing a round of angle data collection, a system unloading test is performed to record the angle recovery state of Wing 02 to ensure the reliability and integrity of the measurement data.

[0031] For the left and right wings 02, the same measurement area division, measurement point layout, data collection process and sampling frequency are used, and time synchronization control is used to ensure that the measurement data of the two wings have a strict correspondence, providing a reliable data basis for subsequent symmetry analysis. This systematic angle measurement method, combined with the technical features of multi-point layout, repeated measurement and synchronous collection, can comprehensively and accurately obtain the deformation characteristic data of wing 02.

[0032] 3.2 Displacement data collection: While collecting angle data, measure the displacement changes of wing 02 under different loads. Use a displacement measuring device to record the displacement value of the wing tip of wing 02 under each level of load. During the displacement measurement process, the stability of the measurement reference should be ensured to avoid displacement of the fixed end of wing 02. For each level of load, multiple displacement measurements are performed to improve data reliability, and the real-time curve of displacement changing with load is recorded. At the same time, monitor the overall deformation trend of wing 02 under load to ensure the continuity and stability of the deformation process. After completing the loading measurement, record the displacement recovery data during the unloading process to evaluate the deformation recovery characteristics of wing 02. Use the same displacement measurement scheme for the left and right wings 02 to ensure the comparability of the measurement data.

[0033] 4. Data Processing and Analysis 4.1 Data preprocessing: The collected angle and displacement data are preprocessed, including data screening, outlier processing and data smoothing. First, the original data is screened to remove obviously abnormal data points. For data that are repeatedly measured, statistical methods are used to determine their effective values. Necessary corrections are made to the measured data to eliminate the influence of measurement system errors and environmental factors.

[0034] 4.2 Characteristic Analysis: Based on the processed data, the strength characteristics of wing 02 at each measurement point are analyzed. The stiffness characteristics under different loads are calculated to evaluate the deformation uniformity of wing 02. By analyzing the load-deformation relationship curve, the linear deformation range of wing 02 is determined. The angle change law of each measurement point is compared to evaluate the strength distribution characteristics of wing 02 along the span direction.

[0035] 4.3 Matching evaluation: For the left and right wings 02, the angle difference and displacement difference of the corresponding measurement points are calculated to evaluate their symmetry. The deformation consistency of the wings 02 on both sides under the same load is analyzed, and the discrete degree of key parameters is calculated. Based on multiple evaluation indicators, a comprehensive scoring mechanism is established to quantify the matching degree of the wings 02 on both sides.

[0036] 5. Screening Decisions 5.1 Eligibility determination: According to the preset technical standards, the test results of Wing 02 are qualified. The judgment content includes key indicators such as maximum deformation, deformation uniformity, and residual deformation. For Wing 02 that does not meet the requirements, the reasons for failure are analyzed to provide a basis for subsequent process improvements.

[0037] 5.2 Matching screening: Perform matching analysis on the wing 02 that has passed the qualification judgment. Sort all possible wing 02 combinations based on the comprehensive scoring results. Select the wing 02 combination with the highest matching degree as the optimal matching pair. At the same time, record the suboptimal matching combination to provide alternative solutions for practical application.

[0038] Embodiment 2: This embodiment provides a device for measuring the strength characteristics of fixed-wing UAV wings and for symmetry matching and screening. The device is mainly used to detect the characteristic changes of the surface shape (such as curvature, stiffness and strength) of the material in the segmented area of ​​wing 02 (wing 02 refers to the mutually symmetrical left wing or right wing) under the same mechanical stress. For some UAVs with higher requirements for wing 02, it is necessary to further accurately measure and compare the surface deformation of the wing-body partition.

[0039] The test device is mainly composed of a support frame 10 with horizontal adjustment, a graded stress generating counterweight module 20, an XY measurement platform positioning mechanism 30, a wingtip height measuring ruler 40, a wing-body partition angle measurement component, a wing-body partition deformation measurement component 50 and a computer processing system.

[0040] The support frame 10 is used as the basic support structure of the whole device, and a mounting seat 03 for mounting the wing 02 is provided on one side of the upper part thereof. The graded stress generating counterweight module 20 is used to apply a test load on the wing 02.

[0041] The XY-axis measuring platform positioning mechanism 30 includes an X-axis moving structure 31 and a Y-axis moving structure 32. The X-axis moving structure 31 includes a horizontal X-axis guide rail 311, a slider 312, a drive motor 313 and a crossbeam frame 314. The horizontal X-axis guide rail 311 is fixed to the support frame 10, and the slider 312 is slidably connected to the horizontal X-axis guide rail 311 through a rolling bearing. The drive motor 313 drives the slider 312 to reciprocate on the horizontal X-axis guide rail 311 through a synchronous belt transmission mechanism. The crossbeam frame 314 is fixed to the slider 312 and is used to support the Y-axis moving structure 32.

[0042] The Y-direction moving structure 32 includes a horizontal Y-direction guide rail 321, a moving seat 322 and a driving device (not shown in the figure). The horizontal Y-direction guide rail 321 is fixed on the crossbeam frame 314, perpendicular to the direction of the horizontal X-direction guide rail 311. The moving seat 322 is slidably connected to the horizontal Y-direction guide rail 321 through a linear bearing. The driving device can adopt a prior art, such as a lead screw nut pair structure, to drive the moving seat 322 to move on the horizontal Y-direction guide rail 321.

[0043] The wing-body partition deformation measurement assembly 50 is connected to the moving seat 322 of the Y-axis moving structure 32, and is used to measure the deformation of the wing 02 surface. Its main body is a lattice frame 51, which is made of lightweight and high-strength material. A plurality of regular vertical through holes are arranged in the lattice frame 51, and these through holes are evenly distributed in a matrix. A cross-connected and interconnected airbag system is arranged around each through hole. The airbag system is made of a wear-resistant and airtight rubber material, and the hole wall diameter of the through hole can be accurately adjusted by inflation and deflation: when inflated, the airbag expands to reduce the hole wall diameter, and when deflated, the airbag contracts to restore the hole wall diameter.

[0044] A deformation measurement component rod 52 is inserted in each through hole, and a marking point is provided on the top thereof for position tracking. The side wall of the lattice frame 51 is provided with an air inlet 53 and an air outlet 54, both of which are connected to the internal airbag system. One-way valves are respectively provided at the air inlet 53 and the air outlet 54 to prevent accidental air leakage from affecting the measurement accuracy. When the airbag is filled with gas, the expansion of the airbag will evenly squeeze the deformation measurement component rod 52, so that it can stably hover in the through hole; when the gas in the airbag is discharged, the airbag shrinks, and an appropriate gap is generated between the airbag and the deformation measurement component rod 52, so that the deformation measurement component rod 52 can fall freely along the through hole. The inflation pressure of the airbag can be adjusted according to the measurement requirements.

[0045] The measurement process specifically includes the following steps: first, the wing 02 is fixedly mounted on the support frame 10, and then the preset stress is applied through the graded stress generating counterweight module 20 and basic data is collected. Then, through the coordinated movement of the X-direction moving structure 31 and the Y-direction moving structure 32, the wing-body partition deformation measurement assembly 50 is accurately positioned directly above the sub-area to be measured of the wing 02. During measurement, the deformation measurement component rods 52 are sequentially dropped to the surface of the wing 02 by controlling the airbag system, and the end points of the multiple measurement component rods 52 jointly form a three-dimensional curved surface shape reflecting the bending of the wing 02.

[0046] To ensure measurement accuracy, the wing-body partition deformation measurement assembly 50 is equipped with a height adjustment structure 55. The structure adopts a cylinder design, which can drive the entire assembly to perform precise up and down position adjustment. A retraction plate 80 is set on the support frame 10, which is used to reliably reset the deformation measurement component rods 52 at different heights back to the initial state. The system uses a high-definition camera device to record the spatial position of the top mark point of the deformation measurement component rod 52 in real time. Combined with computer image processing technology, it can accurately obtain the three-dimensional deformation data of the surface of the wing 02. Finally, this data is fused and analyzed with the data collected by the angle sensing element, and the overall reliability of the measurement results is improved through data complementarity. All measurement data are transmitted to the computer processing system in real time for analysis and processing.

[0047] Furthermore, in the deformation measurement of fixed-wing wings, the wing root area has particularity. Compared with the large deformation of the wing body under load, the wing root area has a smaller deformation due to its structural characteristics and force distribution, usually within 8 mm at most. However, as the connection between the wing and the fuselage, the wing root area not only has the largest area, but is also the key node for force transmission of the entire wing. Its slight deformation has a decisive influence on the overall strength characteristics and flight safety of the wing. Considering that the wing-body partition deformation measurement component needs to maintain a large movement space (including mechanical avoidance in linear motion, steering switching when measuring the left and right wings, etc.) to achieve measurement coverage of the entire wing, this embodiment sets a set of conductive fiber network measurement systems specifically for the wing root area on the bottom surface of the lattice frame 51. The system adopts highly sensitive flexible conductive fibers and dense sensor network layout, and cooperates with high-precision strain sensing units to accurately capture the slight deformation of the wing root area under various levels of load, providing more comprehensive data support for evaluating the strength characteristics of the wing and screening the optimal match.

[0048] Specifically, a foldable lightweight support ring 60 is provided at the bottom edge of the lattice frame, and the support ring 60 can be expanded and retracted by a micro motor drive. A conductive fiber network 61 is arranged on the support ring 60, and the network adopts flexible conductive fibers 611 made of graphene / silver nanowire composite materials, which have good ductility and conductive properties. The conductive fibers 611 are arranged in a warp and weft interlaced manner to form a regular sensing grid. A micro strain sensing unit is provided at the intersection of each grid, which is connected to the signal acquisition module through a flexible wire. The diameter of the support ring 60 in the retracted state is equivalent to the bottom surface of the lattice frame, and the diameter in the expanded state is 20% larger than the bottom surface of the lattice frame, ensuring that the complete measurement area can be covered.

[0049] During operation, first, according to the method of Example 2, the position data of the key measurement points in the wing-body area are obtained through the deformation measurement component rod 52. When measuring to the wing root area, the support ring 60 is controlled to unfold so that the conductive fiber network 61 is evenly attached to the wing surface. The counterweight module applies various levels of load to the wing, and the conductive fiber network 61 deforms along the wing surface. The deformation data of each grid node is collected in real time through the strain sensing unit. After these data are processed by the signal acquisition module, a high-precision deformation distribution cloud map of the wing root area can be obtained.

[0050] This measurement scheme ensures the measurement accuracy of large-scale deformation of the wing body and can accurately capture the subtle deformation characteristics of the wing root area through the coordinated work of the rigid measurement component and the flexible conductive network. Since the conductive fiber 611 has moderate elasticity, as long as the contact part of the deformation measurement component rod 52 is designed to be a smooth arc and the gravity is greater than the elastic force of the conductive fiber 611, the two measurement systems can work together without interfering with each other. Especially when matching the symmetry of the left and right wings, the accurate deformation data of the wing root area provides a key basis for selecting the optimal matching combination.

[0051] Example 3: Wing strength characteristics measurement method based on three-dimensional surface reconstruction This embodiment provides a wing strength characteristic measurement method based on three-dimensional surface reconstruction based on the measurement device described in Example 2. The method realizes accurate measurement and matching screening of the strength characteristics of wing 02 by automatically controlling the operation of the measurement device. The specific implementation steps are as follows: The measurement system first performs self-test and initialization, including checking the airtightness of the airbag system, the reset state of the deformation measurement component rod 52, the motion control system of the X-axis moving structure 31 and the Y-axis moving structure 32, and the working state of the high-definition camera device. After confirming that all systems are normal, the wing 02 is installed on the mounting seat 03 of the support frame 10, and the measurement area is divided on the surface of the wing 02 to determine the location of the key measurement points.

[0052] During the measurement process, the system controls the graded stress generating counterweight module 20 to apply loads step by step according to a preset program. For each level of load, the wing-body partition deformation measurement assembly 50 is accurately positioned above each area to be measured on the wing 02 through the coordinated movement of the X-axis moving structure 31 and the Y-axis moving structure 32. During the positioning process, the control system accurately adjusts the height adjustment structure 55 according to the position characteristics of the area to be measured, so that the lattice frame 51 is maintained at the optimal measurement height. During measurement, the system controls the inflation and deflation of the airbag according to a predetermined sequence, so that the deformation measurement component rod 52 falls down in sequence to contact each measurement point on the surface of the wing 02, and at the same time, the spatial position data of the mark point at the top of the deformation measurement component rod 52 is collected through a high-definition camera.

[0053] The computer processing system receives and processes the measurement data in real time, and reconstructs the three-dimensional deformation surface of the wing 02 surface through image processing algorithms. The system also collects the measurement data of the angle sensing element, and uses a data fusion algorithm to complement and integrate the two measurement data to improve the accuracy of the measurement results. For each load level, the system saves complete measurement data, including load value, displacement data, angle data, and spatial coordinate information of each measurement point.

[0054] After completing a measurement area, the control system resets the deformation measurement component rod 52 by retracting the plate 80 and moves to the next measurement area to continue measurement. During the entire measurement process, the system continuously monitors the measurement status, including key parameters such as airbag pressure, load stability, and displacement sensor data. When an abnormal condition is detected, the system automatically pauses the measurement and performs fault diagnosis.

[0055] For the measurement of the left and right wings 02, the system uses exactly the same measurement parameters and processes to ensure the comparability of the measurement data. After the measurement is completed, the system conducts a comprehensive analysis of the collected data, calculates various characteristic parameters, evaluates the matching degree of the left and right wings, and finally generates a detailed test report to provide data support for the matching screening of the wings.

Claims

1. A method for measuring and symmetric matching the wing strength characteristics of a fixed-wing UAV, characterized in that: A measuring device including a support frame, a graded stress generating counterweight module, an XY measurement platform positioning mechanism and a wing-body partition deformation measurement assembly is used, wherein: The wing-body partition deformation measurement assembly includes a lattice frame provided with a plurality of vertical through holes, an airbag system arranged around the vertical through holes, and a deformation measurement component rod penetrating the vertical through holes, wherein a marking point is provided at the top end of the deformation measurement component rod; The method comprises the following steps: S1. System initialization and wing installation: Checking the air tightness of the airbag system, the reset state of the deformation measurement component rod, and the working state of the camera device; The wing to be tested is fixedly mounted on the mounting seat of the support frame; S2. Multi-dimensional measurement data collection: Divide the wing surface into multiple measurement areas from the wing handle to the wing tip; The wing is loaded in stages by the graded stress generating counterweight module. Under each load stage: Collect angle change data of each measurement area through an angle sensor; Collect the displacement value of the wing tip; Controlling the airbag system so that the deformation measurement component rod array contacts the wing surface in sequence; Acquire the spatial position data of the marking point at the top end of the deformation measurement component rod by the camera device; S3. Data processing and strength characteristics analysis: Perform fusion processing on the collected angle data, displacement value and three-dimensional deformation data; Reconstruct the three-dimensional deformed surface of the wing surface; Calculate the stiffness characteristics and strength distribution of the wing under different loads; S4, symmetry matching screening: The same measurement parameters and process are used to measure the symmetrical wing on the other side; Calculate the angle difference, displacement difference and deformation difference of the corresponding measuring points on both sides of the wings; Establish a comprehensive scoring mechanism that includes strength property consistency and deformation symmetry; The best matching wing combination is selected based on the comprehensive scoring results.

2. The method for measuring and symmetric matching the wing strength characteristics of a fixed-wing UAV according to claim 1 is characterized in that: The XY measurement platform positioning mechanism comprises: The X-direction moving structure comprises a horizontal X-direction guide rail arranged on the support frame, a slider slidably connected to the horizontal X-direction guide rail, and a crossbeam frame fixed on the slider; The Y-direction moving structure comprises a horizontal Y-guide rail fixed on the crossbeam frame and perpendicular to the horizontal X-guide rail, and a moving seat slidably connected to the horizontal Y-guide rail; The wing-body partition deformation measurement component is connected to the moving seat.

3. The method for measuring and symmetric matching the wing strength characteristics of a fixed-wing UAV according to claim 1 is characterized in that: The wing-body partition deformation measurement assembly also includes: A height adjustment structure, used to adjust the height position of the lattice frame; The side wall of the lattice frame is provided with an air inlet and an air outlet communicated with the air bag system, and both the air inlet and the air outlet are provided with a one-way valve.

4. The method for measuring and symmetric matching the wing strength characteristics of a fixed-wing UAV according to claim 1 is characterized in that: The division of the measurement area in step S2 includes: Determine the location of key measurement points based on the structural characteristics of the wing; Increase the number of measurement points in areas with large airfoil changes; Mark the measurement reference at each determined measurement point.

5. The method for measuring and symmetric matching the wing strength characteristics of a fixed-wing UAV according to claim 1 is characterized in that: The hierarchical loading in step S2 includes: Formulate a graded loading plan including load level, loading time, and stabilization time; Apply loads step by step according to preset loading levels; After each level of load application is completed, a predetermined stabilization time is maintained; Real-time monitoring and recording of load values ​​and load stability at all levels.

6. The method for measuring and symmetric matching the wing strength characteristics of a fixed-wing UAV according to claim 1 is characterized in that: After completing the measurement of one measurement area, the deformation measurement component rod is reset to the initial state by retracting the abutment plate, and the XY measurement platform positioning mechanism is controlled to move to the next measurement area.

7. The method for measuring and symmetric matching the wing strength characteristics of a fixed-wing UAV according to claim 1 is characterized in that: The data fusion processing in step S3 includes: Eliminate outliers from the collected angle data, displacement values ​​and three-dimensional deformation data; Process the measurement data using data smoothing algorithms; A multi-source data fusion algorithm is used to integrate angle data, displacement values ​​and three-dimensional deformation data.

8. The method for measuring and symmetric matching the wing strength characteristics of a fixed-wing UAV according to claim 1, characterized in that: The comprehensive scoring mechanism in step S4 includes: Calculate the difference in stiffness characteristics of the wings on both sides under various levels of load; Analyze the deformation symmetry deviation of the wings on both sides; Evaluate the consistency of strength distribution on both wings; The comprehensive matching score is calculated based on the preset weights.

9. A fixed-wing UAV wing strength characteristic measuring device, characterized in that: include: A support frame, wherein a mounting seat for mounting the wing is provided on the support frame; a graduated stress-generating weight module for applying controlled test loads on the wing; An angle measuring device, used to collect angle data of wing deformation; A displacement measuring device for measuring the deformation of the wing tip; XY measurement platform positioning mechanism, including: The X-direction moving structure comprises a horizontal X-direction guide rail arranged on the support frame, a slider slidably connected to the horizontal X-direction guide rail, a driving motor for driving the slider to move on the horizontal X-direction guide rail, and a crossbeam frame fixed on the slider; The Y-direction moving structure comprises a horizontal Y-direction guide rail fixed on the crossbeam frame and perpendicular to the horizontal X-direction guide rail, a moving seat slidably connected to the horizontal Y-direction guide rail, and a driving device for driving the moving seat to move on the horizontal Y-direction guide rail; The wing-body partition deformation measurement assembly is connected to the moving seat and includes: A lattice frame, wherein a plurality of vertical through holes distributed in a matrix are provided in the lattice frame; An airbag system, arranged around the vertical through hole, for controlling the lifting and lowering of the deformation measurement component rod; A plurality of deformation measurement component rods are respectively inserted into the vertical through holes, and the top ends of the rods are provided with marking points for spatial position tracking; A height adjustment structure, used to adjust the height position of the lattice frame; A high-definition camera device, used to record the spatial position information of the marking point in real time; The processor is used for fusing the angle data, displacement data and three-dimensional deformation data.

10. The fixed-wing UAV wing strength characteristic measuring device according to claim 9, characterized in that: It also includes a retraction plate arranged on the support frame, which is used to reset the deformation measurement component rod to an initial state.

Images