Fixed-wing UAV wing strength characteristics measurement and symmetry matching screening device

Abstract

The present invention relates to the technical field of unmanned aerial vehicle manufacturing quality inspection, and provides a fixed-wing unmanned aerial vehicle wing strength characteristic measurement and symmetry matching screening device, comprising a support frame, a graded stress generating counterweight module, a lockable and reversible counterweight fixture positioning mechanism, a wingtip height measuring ruler, and a computer processing system. The support frame is provided with a mounting seat for fixing the wing handle; the graded stress generating counterweight module comprises a plurality of counterweight structures, each of which comprises an upper and a lower clamping member, and the lower clamping member is connected to a load-bearing plate; the counterweight fixture positioning mechanism adopts a bidirectional moving structure, including two groups of X-direction moving structures and a Y-direction moving structure. The present invention obtains the wing force deformation data through multiple measurement means, and adopts a dual screening mechanism of "qualified first and then matched", so as to realize the accurate measurement of the wing strength characteristics and the optimal symmetry matching, and improve the flight performance and reliability of the fixed-wing unmanned aerial vehicle.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle manufacturing quality inspection, and in particular to a fixed-wing unmanned aerial vehicle wing strength characteristic measurement and symmetry matching screening device, which is mainly used to detect and evaluate the strength characteristics of the wing and realize the optimal matching screening of the left and right wings. Background Art

[0002] With the rapid development of UAV technology, fixed-wing UAVs are increasingly used in military reconnaissance, agricultural plant protection, surveying and mapping, and other fields. As a key component of UAVs, the strength characteristics and symmetry of the wing directly affect flight performance and safety. At present, although the manufacturing process and materials of fixed-wing UAV wings are constantly being optimized, due to factors such as material errors and process fluctuations in the production process, even wings produced in the same batch often have different strength characteristics. This difference will cause asymmetric deformation of the wings on both sides during flight, affecting flight stability and control accuracy.

[0003] At present, some wing strength testing devices have been developed and used. For example, the Chinese utility model patent with patent number CN 219890958 U discloses a wing compression testing 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 tested. Although the device can complete the basic compression testing function, it still has obvious shortcomings.

[0004] The existing technology generally has the following problems:

[0005] 1. Single measurement method: Currently, commonly used wing strength detection methods (including the above-mentioned CN 219890958 U patent) mainly rely on a single clamping pressure test or simple deformation observation, which cannot fully obtain the deformation characteristics of the wing during the force process. This method is difficult to accurately reflect the actual strength distribution of each area of ​​the wing and is prone to missing local strength anomalies.

[0006] 2. Insufficient symmetry assessment: Traditional wing screening mainly focuses on whether a single wing meets the strength requirements, and lacks a systematic assessment of the matching degree of strength characteristics of the left and right wings. Even if batch testing is used (such as the simultaneous testing of multiple wings to be tested mentioned in patent CN 219890958U), it is impossible to effectively evaluate and screen out wing pairs with matching strength characteristics. This results in the possibility that even if a single wing meets the strength standard, the assembled drone may still have unstable flight problems.

[0007] 3. Limited measurement accuracy: Most existing measurement devices use mechanical pressure detection or simple electronic measurement tools, which are not accurate and timely enough. At the same time, the lack of effective positioning mechanism and precise force control means during the measurement process can easily lead to systematic errors and affect the reliability of the measurement results.

[0008] 4. Insufficient data processing capabilities: Existing technologies often lack a complete data acquisition and processing system, making it impossible to conduct real-time analysis and comprehensive evaluation of measurement data, making it difficult to achieve accurate matching and optimal screening of wing strength characteristics. In particular, when multiple measurement parameters need to be evaluated simultaneously, existing devices cannot provide effective data fusion and analysis capabilities.

[0009] The existence of these technical problems restricts the performance improvement and product quality stability of fixed-wing UAVs. Summary of the invention

[0010] The purpose of the present invention is to solve the shortcomings of the prior art. The present invention provides a fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device based on graded counterweight loading and multi-point deformation measurement. Various data of the wing when it is subjected to force and deformation are obtained through multiple measurement means such as angle sensing elements, wingtip height measuring rulers, and deformation measurement component rods. A dual screening mechanism of "qualified first and then matched" is adopted to achieve accurate detection of wing quality and optimal symmetry matching.

[0011] In order to solve the above problems, the present invention adopts the following scheme: a fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device, comprising:

[0012] A support frame, one side of the upper portion of which is provided with a mounting seat, the mounting seat being used to fix the wing handle;

[0013] The graded stress generating counterweight module comprises a plurality of counterweight structures, each of which comprises an upper clamping member and a lower clamping member for clamping the upper and lower surfaces of the wing, and a bearing plate for mounting a counterweight is connected to the lower end of the lower clamping member;

[0014] A lockable and reversible counterweight fixture positioning mechanism, comprising two sets of X-direction moving structures installed on the upper part of the support frame, the two sets of X-direction moving structures are connected by a crossbeam frame, and a Y-direction moving structure is provided on the crossbeam frame; and a wingtip height measuring ruler installed in the Y-direction moving structure;

[0015] Wherein, an angle sensing element is installed in the upper clamping member, which is used to sense the angle change data during the wing deformation process in real time;

[0016] The device also includes a computer processing system for real-time acquisition and processing of the displacement values ​​measured by the wingtip height measuring ruler and the angle change data collected by the angle sensing element, and for screening out qualified wings by first comparing the measurement data of a single wing with a preset qualified standard, and then performing pairing tests on the qualified wings in pairs, analyzing the bending angle difference and the wingtip displacement difference at the corresponding loading positions, and finally screening out wing pairs with matching strength characteristics.

[0017] Beneficial effects: This device adopts a graded stress-generating counterweight module and a clamping structure with angle sensing, combined with a locking and reversing positioning mechanism and a computer processing system, which not only achieves accurate measurement of wing strength characteristics, but also ensures the quality matching of wing pairs through a dual screening mechanism of "qualified first and then matched". The overall solution overcomes the shortcomings of the traditional measurement method of singleness and low efficiency, and significantly improves the measurement accuracy and screening effect.

[0018] Preferably, an upper clamping member positioning seat is provided at the lower end of the crossbeam frame, a side wall of the upper clamping member positioning seat close to the wing is parallel to the wingtip edge, a positioning hole is provided on the upper clamping member, and a positioning rod cooperating with the positioning hole is provided at the lower end of the upper clamping member positioning seat.

[0019] Beneficial effect: By arranging an upper clamping piece positioning seat with a positioning rod at the lower end of the crossbeam frame, and making its side wall parallel to the edge of the wing tip, and cooperating with the positioning hole on the upper clamping piece, a precise positioning matching structure is formed. This design not only ensures the accuracy of the installation position of the upper clamping piece, but also improves the installation repetitive accuracy, effectively reduces human operation errors, and improves the reliability of measurement data.

[0020] Preferably, the upper clamp is made of carbon fiber material. The upper clamp is made of carbon fiber material, which has the characteristics of light weight and high strength, which can minimize the influence of the upper clamp's own weight on the measurement result and ensure the stability of the clamping structure, thereby improving the accuracy and reliability of the measurement system.

[0021] Preferably, the X-axis moving structure and the Y-axis moving structure are screw drive structures. Beneficial effects: The X-axis and Y-axis moving structures adopt screw drive, which not only has precise positioning capability and runs smoothly without vibration, but also has the characteristics of simple structure and convenient maintenance, and can ensure the stability and reliability of the positioning system during the measurement process.

[0022] Preferably, it also includes a wing-body partition deformation measurement component, which is connected to the Y-direction movable structure, including: a lattice frame, in which a plurality of regular vertical through holes are arranged, and each through hole is surrounded by cross-connected and interconnected airbags; a plurality of deformation measurement component rods, respectively inserted in the vertical through holes; and air inlets and air outlets, which are arranged on the side walls of the lattice frame and are connected to the airbags. Beneficial effect: The wing-body partition deformation measurement component adopts a lattice frame structure with airbag control and a deformation measurement component rod combination design, which can simultaneously obtain deformation data of multiple measurement points on the wing surface. This design provides more comprehensive and accurate wing strength characteristic information, greatly improving the accuracy of wing pair matching screening.

[0023] Preferably, the wing-body partition deformation measurement assembly is equipped with a height adjustment structure, which is connected to the Y-direction movable structure to drive the entire assembly to adjust up and down. Beneficial effect: The height adjustment structure equipped with the wing-body partition deformation measurement assembly can adapt to wings in different deformation states, ensure that the measurement assembly is always in the best working position, improve the adaptability and measurement accuracy of the measurement system, and make the measurement process more flexible and reliable.

[0024] Preferably, the support frame is provided with a return plate for resetting the deformation measurement component rods at different heights back to the initial state. Beneficial effect: The return plate provided on the support frame cleverly solves the problem of resetting the deformation measurement component rods, enables the measurement system to quickly complete the measurement cycle, significantly improves the work efficiency, and ensures the continuous and stable operation of the measurement system.

[0025] Preferably, the vertical through holes in the lattice frame are evenly distributed in a matrix, and the diameter of the deformation measurement component rod is smaller than the minimum diameter of the through hole. Beneficial effect: The lattice frame adopts a design of evenly distributed vertical through holes in a matrix, and the deformation measurement component rod with a diameter smaller than the through hole provides a higher measurement resolution and ensures the smooth fall of the measurement rod, thereby improving the accuracy and reliability of deformation measurement.

[0026] Preferably, the airbag is made of rubber material, and the air inlet and the air outlet are respectively provided with a one-way valve. Beneficial effect: The airbag made of rubber material and the air inlet and outlet design equipped with a one-way valve ensure that the airbag system has good air tightness and durability, effectively prevents accidental air leakage, and improves the stability and reliability of the entire control system.

[0027] Preferably, the top of the deformation measurement component rod is provided with a marking point. Beneficial effect: The design of setting the marking point at the top of the deformation measurement component rod provides an additional way for the measurement system to collect data visually, and through the data complementarity of multiple measurement methods, the reliability and accuracy of the measurement results are further improved.

[0028] Compared with the prior art, the technical solution of the present invention has the following advantages:

[0029] The graded counterweight loading system, multi-point deformation measurement system and intelligent data processing system are organically combined. By real-time collection of the wing angle change, wingtip displacement and partition deformation data during the loading process, combined with the dual screening mechanism of "qualified first, then matched", it not only solves the problems of single measurement means, limited accuracy and low efficiency in traditional wing detection methods, but also realizes the accurate quantification of wing strength characteristics and optimal symmetry matching, significantly improving the flight performance and reliability of fixed-wing UAVs, and has strong practical value. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] 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.

[0031] 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;

[0032] Figure 2 It is a structural schematic diagram of the present invention;

[0033] Figure 3 It is a partial structural schematic diagram of the deformation measurement component rod of the present invention returning to the initial state;

[0034] Figure 4 It is a partial structural schematic diagram of the present invention that can show that the upper clamping member positioning seat is in an inclined state;

[0035] Figure 5 The present invention can display a partial structural schematic diagram of the positioning rod;

[0036] Figure 6 is a schematic diagram of measuring the bending angle of the wing loading position in the present invention;

[0037] Figure 7 It is a schematic diagram of measuring the curved surface of the wing in different regions in the present invention;

[0038] Figure 8 Schematic diagram of the conductive fiber network measurement system of the present invention.

[0039] Reference numerals:

[0040] Wing 02, mounting seat 03, screw 04, pressing block 05, supporting frame 10, graded stress generating counterweight module 20, counterweight structure 21, upper clamp 211, lower clamp 212, load-bearing plate 213, counterweight weight 214, lockable and reversible counterweight fixture positioning mechanism 30, X-axis moving structure 31, Y-axis moving structure 32, crossbeam frame 33, slide rail 34, wingtip height measuring ruler 40, wing-body partition deformation measuring assembly 50, lattice frame 51, deformation measuring component rod 52, air inlet 53, air outlet 54, height adjustment structure 55, upper clamp positioning seat 60, positioning hole 71, positioning rod 72, retraction plate 80, iron sheet 90. DETAILED DESCRIPTION

[0041] The following will be combined Figure 1-Figure 8 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.

[0042] Embodiment 1: This embodiment provides a fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device. The device is mainly 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.

[0043] refer to Figure 1-Figure 7 The test device is mainly composed of a support frame 10 with horizontal adjustment, a graded stress generating counterweight module 20, a lockable and reversible counterweight fixture positioning mechanism 30, a wingtip height measuring ruler 40, a wing-body partition angle measuring assembly, a wing-body partition deformation measuring assembly 50, and a computer processing system. Among them, the main component of the wing-body partition angle measuring assembly is an angle sensing element, which is installed in the component of the graded stress generating counterweight module 20 where the angle changes, and is used to sense the angle change (the sensing element is a prior art and is not shown in the figure).

[0044] The support frame 10 serves as the basic support structure of the entire device, and a mounting seat 03 is provided on one side of its upper part. The mounting seat 03 is connected to a screw 04 through a thread, and a pressing block 05 is connected to the lower end of the screw 04. The wing 02 is installed by placing the wing handle of the wing 02 between the bottom of the mounting seat 03 and the pressing block 05, and by tightening the screw 04, the pressing block 05 presses down and tightens the wing handle of the wing 02, thereby achieving a stable installation of the wing 02.

[0045] The graded stress generating counterweight module 20 is composed of multiple groups of counterweight structures 21, each group of counterweight structures includes two upper and lower clamping members. The upper clamping member 211 and the lower clamping member 212 respectively clamp the upper and lower surfaces of the wing 02. A bearing plate 213 is connected to the lower end of the lower clamping member 212, and the bearing plate is used to install a counterweight 214, and the weight of the counterweight is used to apply mechanical stress to the wing 02.

[0046] The angle sensing element is preferably installed in each upper clamping member 211 to sense the angle change data of the upper clamping member 211 in real time during the deformation of the wing 02. When the wing 02 is bent and deformed under the action of the graded stress generating counterweight module 20, the upper clamping members 211 installed at different positions will rotate to different degrees as the wing 02 deforms. Figure 6 As shown, the upper clamping parts 211 arranged in sequence from the wing handle to the wing tip respectively form angles ∠A, ∠B, and ∠C, which reflect the degree of bending deformation of the wing 02 at each loading position. The angle sensing element installed in the upper clamping part 211 collects these angle data in real time, and the strength characteristics of the wing 02 at different loading positions can be obtained. After the collected angle data is input into the computer processing system, the angle difference of the wings 02 on both sides at the corresponding loading positions (i.e., the difference of ∠A, ∠B, and ∠C) can be calculated, thereby evaluating the matching degree of the strength characteristics of the wings 02 on both sides, and providing an important basis for selecting the optimal wing 02 pair.

[0047] Design of lockable and reversible counterweight fixture positioning mechanism 30 (reference Figure 2-Figure 4) adopts a bidirectional movable structure. Two groups of X-direction movable structures 31 that can move along the length direction of the wing 02 are installed on the upper part of the support frame 10, and the two groups of X-direction movable structures 31 are connected by a crossbeam frame 33. A Y-direction movable structure 32 that can move along the width direction of the wing 02 is provided on the crossbeam frame 33, and the wingtip height measuring scale 40 is installed in the Y-direction movable structure 32, and its position can be adjusted by moving and locking the Y-direction movable structure 32. The overall position of the wingtip height measuring scale 40 is located above the wing 02, and the lifting stroke of its measuring actuator must be guaranteed to be greater than the maximum deformation of the wing 02 under the set full load. An upper clamping member positioning seat 60 is provided at the lower end of the crossbeam frame 33 to assist in the precise installation of the upper clamping member 211. The reversing function of the lockable and reversible counterweight fixture positioning mechanism 30 is realized by the rotatable design of the upper clamping member positioning seat 60: when measuring the left wing 02, the upper clamping member positioning seat 60 remains in place; when it is necessary to measure the right wing 02, the upper clamping member positioning seat 60 can be rotated 180 degrees so that its side wall is always parallel to the wingtip edge of the measured wing 02, thereby ensuring that the installation accuracy of the upper clamping member 211 is consistent when measuring the left and right wings 02. The power transmission of the above-mentioned X-direction moving structure 31 and the Y-direction moving structure 32 can adopt existing transmission technology, for example, by cooperating with a motor and a belt transmission mechanism, the belt is fixedly connected to the moving part to realize linear motion, and the specific transmission structure is not repeated here.

[0048] When performing the measurement operation: first, place the wing handle of the wing 02 between the mounting seat 03 and the pressing block 05, and securely install the wing 02 by tightening the screws 04. Then use the X-axis moving structure 31 to move the crossbeam frame 33 to the wing tip position to establish the measurement zero point, and then install the counterweight structure 21 (including the upper and lower clamps) to each preset loading position in turn, and then add the counterweight weights 214 in batches on the load-bearing plate 213 to deform the wing 02. While measuring the bending displacement using the wing tip height measuring ruler 40, the angle sensing elements installed in each upper clamp 211 collect the angle change data. During the test, the computer system collects and processes all measurement data in real time. First, the measured displacement and angle values ​​are compared with the preset qualified standards to select qualified wings 02 that meet the strength requirements; then the qualified wings 02 are tested in pairs, and the matching degree of their strength characteristics is evaluated by analyzing the bending angle difference and wingtip displacement difference at the corresponding loading position, and finally the pair of wings 02 with the most matching strength characteristics is selected. Through this dual screening mechanism of "qualified first and then matched", it is ensured that each pair of wings 02 not only has good matching, but also meets the strength requirements.

[0049] Furthermore, in order to prevent the weight of the upper clamp 211 from exerting excessive pressure on the wing 02 and affecting the measurement accuracy, the upper clamp 211 is made of a lightweight material with sufficient hardness, such as carbon fiber, magnesium alloy, polystyrene foam, etc., and this embodiment preferably uses carbon fiber material.

[0050] Furthermore, to ensure the accuracy of the installation position of the upper clamp 211, a side wall of the upper clamp positioning seat 60 close to the wing 02 is designed to be parallel to the edge of the wing tip. The upper clamp 211 is provided with a positioning hole 71, and the lower end of the upper clamp positioning seat 60 is provided with a positioning rod 72 that matches the positioning hole 71. When the positioning rod 72 is plugged into the positioning hole 71, the side wall of the upper clamp 211 can be ensured to be parallel to the side wall of the positioning seat 60, thereby improving the installation accuracy.

[0051] Furthermore, the X-axis moving structure 31 and the Y-axis moving structure 32 can be a screw structure, a belt structure, a hydraulic drive structure or a pneumatic drive structure. In this embodiment, the X-axis moving structure 31 adopts a belt structure and the two sets of belt structures are driven by the same motor to ensure synchronization, and the Y-axis moving structure 32 adopts a hydraulic drive structure.

[0052] Embodiment 2: For some UAVs with higher requirements for the wing 02, based on the angle comparison in Embodiment 1, it is necessary to further accurately measure and compare the surface deformation of the wing-body partition. To this end, a wing-body partition deformation measurement component 50 is added to the device in Embodiment 1.

[0053] The wing-body partition deformation measurement component 50 is connected to the Y-direction moving structure 32, and its main body is a lattice frame 51. A plurality of regular vertical through holes are arranged in the lattice frame, and cross-connected air bags are arranged around each through hole. The inflation and deflation of these air bags can adjust the hole wall diameter of the through hole: the hole wall diameter is reduced when inflated, and the hole wall diameter is restored when deflated (the air bags inside the lattice frame and the through holes formed are not shown in the figure). A deformation measurement component rod 52 is penetrated in each through hole. The side wall of the lattice frame is provided with an air inlet 53 and an air outlet 54, both of which are connected to the internal air bag. When the air bag is filled with gas, the expansion of the air bag will squeeze the deformation measurement component rod 52, so that it can stably hover in the through hole; when the gas in the air bag is discharged, the air bag shrinks, and a gap is generated between the air bag and the deformation measurement component rod 52, so that the deformation measurement component rod 52 can fall freely along the through hole. In the initial state, the length of the deformation measuring rod 52 located above the airbag is designed to be greater than the maximum displacement of the predicted deformation position of the wing 02.

[0054] Its working process is (reference Figure 8): The wing-body partition deformation measurement assembly 50 is moved to the top of the wing 02 sub-region L3 section through the X-axis moving structure and the Y-axis moving structure, and then the gas in the airbag is discharged through the air outlet 54. As the airbag contracts, the deformation measurement component rod 52 will fall to the upper end of the wing 02. When the upper end of the wing 02 sub-region is covered with the deformation measurement component rod 52, these rods form a curved surface shape that reflects the bending of the wing 02. The same method can be used to obtain the deformation data of the wing 02 in the sub-regions L1 and L2, and all the acquired deformation measurement data will be transmitted to the computer processing system for analysis and processing.

[0055] To ensure the accuracy of the measurement, the wing-body partition deformation measurement assembly 50 is equipped with a height adjustment structure 55, which can drive the entire assembly to adjust up and down, so that it can always move to the top of the deformed wing 02 for measurement. The height adjustment structure 55 is connected to the Y-direction moving structure, and can adopt a screw structure, a hydraulic structure or a cylinder structure. In this embodiment, a cylinder structure is selected.

[0056] During the measurement process, the deformation measurement component rod 52 will fall to different heights, resulting in a reduction in its length above the airbag, which may affect the accuracy of subsequent measurements and even cause the rod to fall out of the grid. To solve this problem, a return plate 80 is provided on the support frame 10 to reset the deformation measurement component rods 52 at different heights back to the initial state.

[0057] The reset process is as follows: when the deformation measurement component rod 52 needs to be restored to the initial state, first ensure that the airbag is filled with gas, and then move all the deformation measurement component rods 52 up to above the return plate 80 through the height adjustment structure 55. Then, the wing-body partition deformation measurement assembly 50 is moved to just above the return plate 80 through the X-axis moving structure and the Y-axis moving structure, and then the gas is discharged through the air outlet 54 to make the deformation measurement component rod 52 fall onto the return plate 80. As needed, the height of the deformation measurement component rod 52 relative to the grid can also be adjusted through the height adjustment structure 55 to ensure that its length above the airbag is greater than the maximum displacement of the wing 02 deformation.

[0058] Furthermore, in order to improve the accuracy of deformation measurement, the vertical through holes in the lattice frame 51 are evenly distributed in a matrix, and the spacing of the through holes can be adjusted according to the measurement accuracy requirements. The deformation measurement component rod 52 is made of a light and high-strength carbon fiber material, and its diameter is smaller than the minimum diameter of the through hole to ensure that it can fall smoothly when the airbag is deflated.

[0059] Furthermore, the airbag is made of a wear-resistant and airtight rubber material, and its inflation pressure is adjustable to adapt to deformation measurement component rods 52 of different diameters. 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.

[0060] Furthermore, a marking point is set at the top of the deformation measurement component rod 52, and the spatial position of the marking point is recorded by a high-definition camera device. In combination with computer image processing technology, the three-dimensional deformation data of the surface of the wing 02 can be obtained more accurately. At the same time, this data is fused and analyzed with the data collected by the angle sensing element to further improve the reliability of the measurement results.

[0061] Furthermore, in the deformation measurement of fixed-wing wings, the wing root area has its own particularity. Compared with the large deformation of the wing body under the action of 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. Refer to Figure 8 The system uses highly sensitive flexible conductive fibers and a dense sensor network layout, combined with high-precision strain sensing units, to accurately capture the tiny deformations of the wing root area under various levels of load, providing more comprehensive data support for evaluating wing strength characteristics and screening for the optimal match.

[0062] Specifically, a foldable lightweight support ring 100 is provided at the bottom edge of the lattice frame, and the support ring 100 can be expanded and retracted by a micro motor drive. A conductive fiber network 110 is arranged on the support ring 100, and the network uses flexible conductive fibers 111 made of a graphene / silver nanowire composite material, which has good ductility and conductive properties. The conductive fibers 111 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 100 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.

[0063] 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 100 is controlled to unfold so that the conductive fiber network 110 is evenly attached to the wing surface. The counterweight module applies various levels of load to the wing, and the conductive fiber network 111 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.

[0064] 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 111 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 111, 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.

Claims

1. A fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device, characterized in that: include: A support frame (10) is provided with a mounting seat (03) on one side of its upper portion, and the mounting seat (03) is used to fix the wing handle; A graded stress generating counterweight module (20) comprises a plurality of counterweight structures (21), each counterweight structure comprising an upper clamping member (211) and a lower clamping member (212) for clamping the upper and lower surfaces of a wing, wherein the lower end of the lower clamping member (212) is connected to a bearing plate (213) for mounting a counterweight (214); A lockable and reversible counterweight fixture positioning mechanism (30) comprises two groups of X-direction movable structures (31) mounted on the upper part of the support frame (10), wherein the two groups of X-direction movable structures (31) are connected via a crossbeam frame (33), and a Y-direction movable structure (32) is disposed on the crossbeam frame (33); and a wingtip height measuring ruler (40) mounted in the Y-direction movable structure (32); Wherein, an angle sensing element is installed in the upper clamping member (211) for real-time sensing of angle change data during wing deformation; The device also includes a computer processing system for real-time acquisition and processing of the displacement value measured by the wingtip height measuring ruler (40) and the angle change data acquired by the angle sensing element, and firstly comparing the measurement data of a single wing with a preset qualified standard to select qualified wings, then performing pairing tests on the qualified wings, analyzing the bending angle difference and the wingtip displacement difference at the corresponding loading position, and finally selecting a wing pair with matching strength characteristics; The invention also comprises a wing-body partition deformation measurement assembly (50), wherein the wing-body partition deformation measurement assembly (50) is connected to the Y-direction movable structure (32), and comprises: A lattice frame (51) is provided with a plurality of regular vertical through holes, and each through hole is surrounded by crossed and interconnected air bags; A plurality of deformation measuring rods (52) are respectively inserted into the vertical through holes; and An air inlet (53) and an air outlet (54) are arranged on the side wall of the lattice frame (51) and are both in communication with the airbag.

2. The fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device according to claim 1 is characterized in that: An upper clamping member positioning seat (60) is provided at the lower end of the crossbeam frame (33), and the upper clamping member positioning seat (60) is close to a side wall of the wing and parallel to the wing tip edge. A positioning hole (71) is provided on the upper clamping member (211), and a positioning rod (72) matching the positioning hole (71) is provided at the lower end of the upper clamping member positioning seat (60).

3. The fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device according to claim 1 is characterized in that: The upper clamping piece (211) is made of carbon fiber material.

4. The fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device according to claim 1 is characterized in that: The X-direction moving structure (31) and the Y-direction moving structure (32) are screw rod transmission structures.

5. The fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device according to claim 1 is characterized in that: The wing-body partition deformation measurement assembly (50) is equipped with a height adjustment structure (55), and the height adjustment structure (55) is connected to the Y-direction movable structure (32) and is used to drive the entire assembly to be adjusted up and down.

6. The fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device according to claim 1 is characterized in that: The support frame (10) is provided with a return plate (80) for resetting the deformation measurement component rods (52) at different heights back to an initial state.

7. The fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device according to claim 1, characterized in that: The vertical through holes in the lattice frame (51) are evenly distributed in a matrix, and the diameter of the deformation measurement component rod (52) is smaller than the minimum diameter of the through holes.

8. The fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device according to claim 1, characterized in that: The airbag is made of rubber material, and the air inlet (53) and the air outlet (54) are respectively provided with a one-way valve.

9. The fixed-wing UAV wing strength characteristic measurement and symmetry matching screening device according to claim 1, characterized in that: The top end of the deformation measurement component rod (52) is provided with a marking point.

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