A high-aspect-ratio heavy wing bending and torsional stiffness measurement platform

Abstract

The present application belongs to the technical field of flexible body aircraft, and particularly relates to a large-aspect-ratio heavy-load lightweight wing bending and torsional stiffness measuring platform. The measuring platform comprises a variable-roots wing clamping table, a telescopic heavy-load support frame, a lifting heavy-load beam, a pre-tightening force regulator, an integrated infusion loading device, a data monitoring terminal and a displacement meter. The lifting heavy-load beam is located directly above the variable-roots wing clamping table and spans the two heavy-load telescopic vertical beams of the telescopic heavy-load support frame. The pre-tightening force regulator is connected to the lifting heavy-load beam and the heavy-load flexible lightweight wing test piece through a pull rope at both ends. The data monitoring terminal is used to monitor and record the displacement and tension data of different measuring points of the lightweight wing test piece. The integrated infusion loading device can accurately control the different loads at different positions of the lightweight wing test piece, and realize the equivalent fine loading of the aerodynamic distributed load of different regions of the heavy-load flexible lightweight wing test piece under different working conditions, thereby greatly improving the loading accuracy.

Description

Technical Field

[0001] This invention belongs to the field of flexible body aircraft technology, specifically relating to a high aspect ratio heavy-load lightweight wing bending and torsional stiffness measurement platform. Background Technology

[0002] Compared to traditional rigid wings, flexible lightweight wings offer significant advantages in terms of cost and weight. During the design phase, meticulous testing of the flexible lightweight wing's bending and torsional stiffness and strength is necessary, especially for high-aspect-ratio, heavy-load, heterogeneous flexible lightweight wings; precise early-stage testing is crucial.

[0003] Currently, there is no dedicated measurement platform or method for the stiffness and static strength of heavy-duty flexible lightweight wings with large aspect ratios. Traditional static strength and stiffness measurement platforms are mainly for rigid wings or lightly loaded lightweight wings. They are generally used to apply equivalent loads by suspending weights at the ends or laying sandbags on the surface of the test piece. This method cannot achieve accurate equivalent loading of wing surface loads under special working conditions, and cannot simultaneously satisfy the equivalence principles of force, moment, and loading point. The test results have strong dispersion.

[0004] Therefore, it is necessary to design a measurement platform capable of measuring the stiffness of heavy-load flexible lightweight wings with large aspect ratios. Summary of the Invention

[0005] In view of this, the present invention provides a high aspect ratio heavy-load lightweight wing bending and torsional stiffness measurement platform. This platform can adapt to the performance testing of heavy-load flexible lightweight wings under different working conditions, while effectively achieving accurate loading based on the principle of loading equivalence.

[0006] To achieve the above objectives, the present invention adopts the following specific technical solution:

[0007] This invention provides a high aspect ratio heavy-duty lightweight wing bending and torsional stiffness measurement platform, which includes a variable wing root wing clamping platform, a telescopic heavy-duty support frame, a lifting heavy-duty crossbeam, a preload adjuster, a data monitoring terminal, an infusion-type integrated loading device, and a displacement gauge.

[0008] The variable wing root wing clamping platform and the telescopic heavy-duty support frame are both fixedly installed on the ground, with the two telescopic heavy-duty support frames located on both sides of the variable wing root wing clamping platform.

[0009] The variable wing root wing clamping platform is used to clamp and fix the wing root of the heavy-load flexible lightweight wing test piece, so that the heavy-load flexible lightweight wing test piece forms a cantilever beam structure.

[0010] The lifting heavy-duty crossbeam is located on top of the variable wing root wing clamping platform and can be slidably installed on the two telescopic heavy-duty support frames in a vertical direction.

[0011] The two ends of the preload adjuster are respectively connected between the lifting heavy-duty crossbeam and the wing surface of the heavy-duty flexible lightweight wing test piece by pull ropes, and are used to adjust the preload of the pull ropes;

[0012] The infusion-type integrated loading device is used to apply aerodynamic equivalent loading to the heavy-load flexible lightweight wing test piece through multiple loading liquid bags distributed along the spanwise direction of the heavy-load flexible lightweight wing test piece, so as to simulate different bending and torsional conditions.

[0013] The displacement gauge is installed on the ground directly below the heavy-load flexible lightweight wing test specimen and is used to measure the displacement of the heavy-load flexible lightweight wing test specimen before and after loading.

[0014] The data monitoring terminal is connected to the infusion-type integrated loading device, the preload adjuster, and the displacement gauge, and is used to monitor and store the preload of each pull rope, the loading load of each loading liquid bag, and the real-time data of each displacement gauge.

[0015] Furthermore, the variable wing root wing clamping platform includes a mold tooling platform, a wing clamping tooling mold, an upper variable wing root mold, and a lower variable wing root mold, all machined from high-strength aluminum alloy.

[0016] The mold tooling table is fixedly installed on the ground and located between the two telescopic heavy-duty support frames;

[0017] The wing clamping tooling mold is slidably installed on the mold tooling table and is provided with a through hole extending in the horizontal direction and perpendicular to the arrangement direction of the two telescopic heavy-duty support frames; the through hole matches the airfoil shape at the wing root of the heavy-duty flexible lightweight wing test piece and is used to accommodate the wing root clamping section of the inflated heavy-duty flexible lightweight wing test piece.

[0018] The upper variable wing root mold and the lower variable wing root mold are vertically opposite each other on the upper and lower sides of the through hole, and are rotatably mounted on the wing clamping fixture mold by hinges; after the upper variable wing root mold and the lower variable wing root mold are connected and locked together, they form a complete wing clamping mold for clamping heavy-duty flexible lightweight wing test pieces.

[0019] Furthermore, the top surface of the mold tooling table is provided with a sliding groove; the lower edge of the wing clamping tooling mold is provided with a sliding tenon; the sliding tenon is slidably installed in the sliding groove, so that the mold tooling table can slide along the spanwise direction of the flexible lightweight wing; the mold tooling table is provided with a scale line on one side of the sliding groove on its top surface, and the scale line is used to measure the sliding distance of the wing clamping tooling mold relative to the mold tooling table;

[0020] The clamping airfoil contour edges of the upper variable airfoil root mold and the lower variable airfoil root mold are designed with large rounded chamfers, which can effectively reduce the risk of cutting the flexible lightweight airfoil when the airfoil root of the heavy-load flexible lightweight airfoil test piece becomes unstable, and improve the accuracy of the instability test.

[0021] Furthermore, the telescopic heavy-duty support frame includes a support frame base, a heavy-duty telescopic vertical beam, and a heavy-duty horizontal beam slide rail;

[0022] The support frame base is fixed to the ground and has a through square hole along the height direction; the heavy-duty telescopic vertical beam is installed in the square hole; the support frame base has a built-in heavy-duty winch, which is used to control the extension and retraction of the heavy-duty telescopic vertical beam along the height direction; the heavy-duty crossbeam slide rail is fixedly installed on the side of the heavy-duty telescopic vertical beam facing the mold tooling table.

[0023] Furthermore, the lifting heavy-duty crossbeam includes two heavy-duty crossbeams and hydraulic cylinders corresponding to each heavy-duty crossbeam;

[0024] The two heavy-duty crossbeams are distributed at intervals in the vertical direction; the heavy-duty crossbeams span between the two telescopic heavy-duty support frames, and their ends are slidably engaged with the slide rails of the two heavy-duty crossbeams; the hydraulic cylinder is installed between the corresponding heavy-duty crossbeam and the support frame base, and is used to drive the corresponding heavy-duty crossbeam to slide in the vertical direction along the slide rail of the heavy-duty crossbeam.

[0025] The middle section of the heavy-duty crossbeam forms a rope tethering post, used to tether the other end of the rope connecting the preload adjuster.

[0026] Furthermore, both ends of the heavy-duty crossbeam are provided with an extension section that is suspended on one side of the heavy-duty telescopic vertical beam, and the outer side of the extension section is welded with a hydraulic rotating lug of the crossbeam.

[0027] The top surface of the support frame base is welded with a hydraulic rotating lug for the support frame; the hydraulic rotating lug for the support frame and the hydraulic rotating lug for the crossbeam are located on the same side of the heavy-duty telescopic vertical beam.

[0028] The bottom end of the hydraulic cylinder is rotatably mounted on the hydraulic rotating lug of the support frame; the piston rod of the hydraulic cylinder is rotatably mounted on the hydraulic rotating lug of the crossbeam.

[0029] The lifting heavy-duty crossbeam is raised and lowered by two independent hydraulic cylinders, thereby enabling independent adjustment of the traction height of the ropes at different positions on the heavy-duty flexible lightweight wing test specimen.

[0030] Furthermore, the infusion-type integrated loading device includes a pump-liquid integrator, multiple loading liquid bags, infusion lines corresponding to each loading liquid bag, and a liquid bag force gauge;

[0031] Multiple liquid bag force gauges are suspended at spanwise intervals on the lower wing surface of the heavy-duty flexible lightweight wing test specimen.

[0032] The bottom end of the liquid bag force gauge is connected to a loading liquid bag;

[0033] The loading fluid bag is connected to the pump-liquid integrator via a corresponding infusion pipeline;

[0034] The pump-liquid integrator is used to control the infusion rate and direction of each infusion line, thereby individually controlling the infusion volume of each loading fluid bag;

[0035] The data monitoring terminal is connected to each liquid bag force gauge and is used to monitor and record the real-time data of the liquid bag force gauge.

[0036] Furthermore, reinforcing metal bonding pieces, corresponding one-to-one with the liquid bag force gauges, are bonded to the lower wing surface of the heavy-duty flexible lightweight wing test piece along its spanwise intervals; the liquid bag force gauges are connected to the corresponding reinforcing metal bonding pieces via ropes.

[0037] Furthermore, the preload adjuster includes a heavy-duty turnbuckle sleeve and a pull-string force gauge;

[0038] The heavy-duty turnbuckle sleeve is threaded to one end of the pull rope force gauge, and the other end of both the heavy-duty turnbuckle sleeve and the pull rope force gauge are connected to a pull rope.

[0039] The preload of the pull rope is adjusted by the threaded connection between the heavy-duty turnbuckle and the pull rope force gauge;

[0040] The data monitoring terminal is connected to each pull rope force gauge and is used to monitor and record the real-time data of the pull rope force gauge.

[0041] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0042] 1. In the high aspect ratio heavy-load lightweight wing bending and torsional stiffness measurement platform of the present invention, the variable wing root wing clamping table realizes the stiffness test of the heavy-load flexible lightweight wing test piece at the variable wing root position, which cannot be achieved by traditional stiffness measurement platforms, through the flip-out upper and lower variable wing root molds. The large chamfer design of the airfoil hole profile effectively reduces the risk of cutting the flexible lightweight wing when the wing root of the heavy-load flexible lightweight wing test piece becomes unstable, and improves the accuracy of the instability state test.

[0043] 2. The high aspect ratio heavy-duty lightweight wing bending and torsional stiffness measurement platform of the present invention can independently adjust the traction height of the rope at different positions of the heavy-duty flexible lightweight wing test piece through two independent hydraulically driven lifting heavy-duty crossbeams, so that the measurement platform has the ability to measure the static strength and instability boundary of the heavy-duty flexible lightweight wing test piece under different stiffness conditions of the heavy-duty flexible lightweight wing at different positions.

[0044] 3. The high aspect ratio heavy-duty lightweight wing bending and torsional stiffness measurement platform of this invention, through its designed pump-fluid integrator, can precisely control different loading levels and progressive loading at different locations on the heavy-duty flexible lightweight wing test specimen. This achieves equivalent and precise loading of aerodynamic load distribution in different areas of the heavy-duty flexible lightweight wing test specimen under different working conditions, greatly improving loading accuracy. Furthermore, the loading liquid bag method can significantly increase the upper limit of loading, meeting the loading requirements for the static strength and stiffness limits of the heavy-duty flexible lightweight wing test specimen.

[0045] 4. The high aspect ratio heavy-duty lightweight wing bending and torsional stiffness measurement platform of the present invention overcomes the problem that traditional inflatable structural component stiffness testing devices cannot adjust the preload of the tension rope. Through the threaded connection between the heavy-duty turnbuckle sleeve and the tension rope force gauge, the preload of the tension rope can be finely adjusted, and the tension rope force gauge connected to it can monitor the preload of the tension rope in real time, so as to achieve the purpose of testing the stiffness and instability boundary of the heavy-duty flexible lightweight wing test piece under different preloads. At the same time, the measurement platform can also be applied to the field of strength and stiffness measurement of ordinary rigid wings, and can be widely used in the field of flexible body aircraft technology. Attached Figure Description

[0046] Figure 1 This is a general layout diagram of the high aspect ratio heavy-load lightweight wing bending and torsional stiffness measurement platform of the present invention;

[0047] Figure 2A and Figure 2B These are schematic diagrams showing the structure of the upper and lower variable wing root molds during flipping and bonding.

[0048] Figure 3A and Figure 3B A schematic diagram of the assembly structure of the telescopic heavy-duty support frame and the lifting heavy-duty crossbeam.

[0049] Figure 4 This is a schematic diagram of the preload adjuster.

[0050] Figure 5 This is a schematic diagram of the structure of an infusion-type integrated loading device;

[0051] Figure 6-10 This is a schematic diagram illustrating the working principle of the high aspect ratio heavy-load lightweight wing bending and torsional stiffness measurement platform of the present invention.

[0052] Figure label:

[0053] 1-Variable wing root wing clamping platform; 2- Telescopic heavy-duty support frame; 3- Lifting heavy-duty crossbeam; 4- Preload adjuster; 5- Data monitoring terminal; 6- Infusion-type integrated loading device; 11- Wing clamping tooling mold; 12- Upper variable wing root mold; 13- Lower variable wing root mold; 14- Through hole; 15- Scale line; 16- Mold tooling platform; 17- Sliding latch; 18- Sliding slot; 21- Support frame base; 22- Heavy-duty telescopic vertical beam; 23- Heavy-duty crossbeam slide rail; 31- Heavy-duty crossbeam; 32-Tethering post; 33-Hydraulic rotating lug of support frame; 34-Hydraulic cylinder one; 35-Hydraulic cylinder two; 36-Piston rod one; 37-Piston rod two; 38-Hydraulic rotating lug of crossbeam; 41-Heavy-duty turnbuckle sleeve; 42-Tethering force gauge; 43-Pull ring; 61-Loading liquid bag; 62-Pump-liquid integrator; 63-Infusion pipeline; 64-Liquid bag force gauge; 101-Tethering rope; 201-Heavy-duty flexible lightweight wing test piece; 202-Inflation pipeline; 601-Displacement gauge. Detailed Implementation

[0054] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0055] In the description of this invention, it should be understood that the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances. Furthermore, in the description of this invention, unless otherwise stated, "multiple" refers to two or more. "And / or" describes the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone. The character " / " generally indicates that the preceding and following related objects have an "or" relationship.

[0056] like Figure 1 As shown, this embodiment of the invention provides a high aspect ratio heavy-duty lightweight wing bending and torsional stiffness measurement platform. The platform includes a variable wing root wing clamping platform 1, a telescopic heavy-duty support frame 2, a lifting heavy-duty crossbeam 3, a preload adjuster 4, a data monitoring terminal 5, an infusion-type integrated loading device 6, a pull rope 101, and a displacement gauge 601; wherein:

[0057] Both the variable wing root clamping platform 1 and the telescopic heavy-duty support frame 2 are fixedly installed on the ground. The two telescopic heavy-duty support frames 2 are located on both sides of the variable wing root clamping platform 1, and can be symmetrically arranged on both sides of the variable wing root clamping platform 1. The variable wing root clamping platform 1 is used to clamp and fix the wing root of the heavy-duty flexible lightweight wing test piece 201, so that the heavy-duty flexible lightweight wing test piece 201 forms a cantilever beam structure with the wing root side fixed and the wingtip side cantilevered. The lifting heavy-duty crossbeam 3 is located on the top of the variable wing root clamping platform 1 and can be vertically and slidably installed between the two telescopic heavy-duty support frames 2. The two ends of the preload adjuster 4 are connected to the upper wing surface of the heavy-duty lifting beam 3 and the heavy-duty flexible lightweight wing test piece 201 via pull ropes 101. That is, one end of the preload adjuster 4 is connected to the heavy-duty lifting beam 3 via pull rope 101, and the other end is connected to the upper wing surface of the heavy-duty flexible lightweight wing test piece 201 via pull rope 101. The preload adjuster 4 is used to adjust the preload of the pull rope 101. In this embodiment, it is illustrated by the example of four pull ropes 101 connected between the heavy-duty lifting beam 3 and the upper wing surface of the heavy-duty flexible lightweight wing test piece 201. Two pull ropes 101 are connected to the middle position of the upper wing surface, and the other two pull ropes 101 are connected to the wingtip position of the upper wing surface. The two pull ropes 101 at the wingtip and the middle position are distributed along the chord direction of the heavy-duty flexible lightweight wing test piece 201. The infusion-type integrated loading device 6 is used to apply aerodynamic equivalent loading to the heavy-duty flexible lightweight wing test piece 201 through multiple loading liquid bags 61 distributed along the spanwise direction of the heavy-duty flexible lightweight wing test piece 201, to simulate different bending and torsional conditions. Multiple displacement gauges 601 are installed on the ground directly below the heavy-duty flexible lightweight wing test piece 201 and are spaced apart along the spanwise direction of the heavy-duty flexible lightweight wing test piece 201. The displacement gauges 601 are used to measure the displacement of the heavy-duty flexible lightweight wing test piece 201 before and after loading. The data monitoring terminal 5 is connected to the infusion-type integrated loading device 6, the preload adjuster 4, and the displacement gauges 601, and is used to monitor and store the preload of each pull rope 101, the loading load of each loading liquid bag 61, and the real-time data of each displacement gauge 601.

[0058] In the aforementioned measurement platform, such as Figure 2A and Figure 2BAs shown, the variable wing root clamping platform 1 includes a mold tooling platform 16, a wing clamping tooling mold 11, an upper variable wing root mold 12, and a lower variable wing root mold 13, all machined from high-strength aluminum alloy. The mold tooling platform 16 can be fixedly installed on the ground by bolts and is located between two telescopic heavy-duty support frames 2. The wing clamping tooling mold 11 is slidably installed on the top surface of the mold tooling platform 16 and is provided with a through hole 14 extending horizontally and perpendicular to the arrangement direction of the two telescopic heavy-duty support frames 2. That is, the through hole 14 penetrates the wing clamping tooling mold 11 along the spanwise direction of the heavy-duty flexible lightweight wing test piece 201; the through hole 14 matches the airfoil shape at the wing root of the heavy-duty flexible lightweight wing test piece 201 and is used to accommodate the wing root clamping section of the inflated heavy-duty flexible lightweight wing test piece 201. Meanwhile, an opening slot (not shown in the figure) communicating with the through hole 14 is also provided on the top surface of the wing clamping tooling mold 11. The opening slot facilitates the exposure of the air nozzle of the heavy-load flexible lightweight wing test piece 201 and connection to the inflation pipe 202. The upper variable wing root mold 12 and the lower variable wing root mold 13 are arranged vertically opposite each other on the upper and lower sides of the through hole 14, and are mounted on the front end of the wing clamping tooling mold 11 by hinge. This allows the upper variable wing root mold 12 to only rotate upward around the hinge relative to the wing clamping tooling mold 11, while the lower variable wing root mold 13 can only rotate downward around the hinge relative to the wing clamping tooling mold 11. After the upper variable wing root mold 12 and the lower variable wing root mold 13 rotate to contact, they fit together and lock together to form a complete wing clamping mold. The clamping airfoil is consistent with the wing root airfoil of the heavy-load flexible lightweight wing test piece 201 and the airfoil of the through hole 14 of the wing clamping tooling mold 11. After the upper variable wing root mold 12 and the lower variable wing root mold 13 are joined, they form mounting holes that match the shape of the corresponding part of the heavy-load flexible lightweight wing test piece 201. This allows the upper variable wing root mold 12 and the lower variable wing root mold 13 to fit together and lock into a complete wing clamping mold for clamping the heavy-load flexible lightweight wing test piece 201. The clamping airfoil contour edges of the upper variable wing root mold 12 and the lower variable wing root mold 13 are designed with large rounded chamfers, which can effectively reduce the risk of cutting the flexible lightweight wing when the wing root of the heavy-load flexible lightweight wing test piece 201 becomes unstable, and improve the accuracy of the instability test.

[0059] like Figure 2A , Figure 2B , Figure 3A and Figure 3BAs shown, the top surface of the mold fixture 16 is provided with two parallel sliding slots 18. The lower edge of the wing clamping fixture mold 11 is provided with sliding tenons 17 corresponding to the two sliding slots 18. The cross-sectional shape of the sliding tenons 17 and the sliding slots 18 is an inverted T-shape. The sliding tenons 17 are slidably installed in the sliding slots 18, and the sliding tenons 17 and the sliding slots 18 are engaged and slidably connected, so that the mold fixture 16 can slide along the spanwise direction of the flexible lightweight wing, and the wing clamping fixture mold 11 can be locked to the mold fixture 16 by bolts, pins or other locking mechanisms. The mold fixture 16 is provided with a scale line 15 on one side of the sliding slots 18 on its top surface. The scale line 15 is used to measure the sliding distance of the wing clamping fixture mold 11 relative to the mold fixture 16. The sliding distance of the wing clamping fixture mold 11 can be observed intuitively through the scale line 15.

[0060] like Figure 2A , Figure 2B , Figure 3A and Figure 3B As shown, the telescopic heavy-duty support frame 2 includes a support frame base 21, a heavy-duty telescopic vertical beam 22, and a heavy-duty horizontal beam slide rail 23. The support frame base 21 is fixed to the ground by bolts and has a through square hole along the height direction. The heavy-duty telescopic vertical beam 22 is installed in the square hole. The support frame base 21 has a built-in heavy-duty winch, which is used to control the extension and retraction of the heavy-duty telescopic vertical beam 22 along the height direction. The heavy-duty horizontal beam slide rail 23 is fixedly installed on the side of the heavy-duty telescopic vertical beam 22 facing the mold tooling table 16.

[0061] like Figure 3BAs shown, the lifting heavy-duty crossbeam 3 includes two heavy-duty crossbeams 31 and hydraulic cylinders corresponding to each heavy-duty crossbeam 31. The two heavy-duty crossbeams 31 are spaced apart in the vertical direction. The heavy-duty crossbeams 31 span between two telescopic heavy-duty support frames 2, and both ends are slidably engaged with the heavy-duty crossbeam slide rail 23 through sliding grooves. The sliding grooves are tightly engaged with the heavy-duty crossbeam slide rail 23, and the heavy-duty crossbeams 31 can only slide along the height direction of the heavy-duty telescopic vertical beam 22. The hydraulic cylinders are installed between the corresponding heavy-duty crossbeams 31 and the support frame base 21, and are used to drive the corresponding heavy-duty crossbeams 31 to slide vertically along the heavy-duty crossbeam slide rail 23. The middle section of the heavy-duty crossbeam 31 forms a rope tethering post 32, which is used to tether the rope 101 connected to the preload adjuster 4. One end of the rope 101 is tied to the rope tethering post 32 of the two heavy-duty crossbeams 31, and the other end is tied to the preload adjuster 4. In this embodiment, the two heavy-duty crossbeams 31 are an upper heavy-duty crossbeam located on the upper side and a lower heavy-duty crossbeam located on the lower side; the hydraulic cylinders correspond one-to-one with the heavy-duty crossbeams 31; the two hydraulic cylinders are hydraulic cylinder one 34 corresponding to the upper heavy-duty crossbeam and hydraulic cylinder two 35 corresponding to the lower heavy-duty crossbeam; hydraulic cylinder one 34 has a cylinder body one and a piston rod one 36; hydraulic cylinder two 35 has a cylinder body two and a piston rod two 37. Each heavy-duty crossbeam 31 has an extension section suspended on one side of the heavy-duty telescopic vertical beam 22 at both ends, that is, each end of the heavy-duty crossbeam 31 has an extension section suspended on the rear side of the heavy-duty telescopic vertical beam 22; the extension section can be a right-angled plate structure that fits against the heavy-duty telescopic vertical beam 22; a crossbeam hydraulic rotating lug 38 is welded to the outer side of the extension section, and only one crossbeam hydraulic rotating lug 38 can be welded to the outer side of the extension section of each heavy-duty crossbeam 31. A support frame hydraulic rotating lug 33 is welded to the rear side of the top surface of the support frame base 21, such as Figure 3BAs shown, a hydraulic rotating lug 33 is fixed to the trailing edge of the upper surface of the support frame base 21 on both sides of the variable wing root wing clamping platform 1. The hydraulic rotating lug 33 and the hydraulic rotating lug 38 of the crossbeam are located on the same side of the heavy-duty telescopic vertical beam 22. In this embodiment, the side where the hydraulic rotating lug 33 and the hydraulic rotating lug 38 of the crossbeam are located is defined as the rear side of the heavy-duty telescopic vertical beam 22, and the heavy-duty flexible lightweight wing test piece 201 is installed on the front side of the heavy-duty telescopic vertical beam 22. The bottom end of the hydraulic cylinder is rotatably mounted on the hydraulic rotating lug 33 of the support frame, and the piston rod of the hydraulic cylinder is rotatably mounted on the hydraulic rotating lug 38 of the crossbeam. That is, a cylinder body one is rotatably mounted on one hydraulic rotating lug 33 of the support frame, and a cylinder body two is rotatably mounted on the other hydraulic rotating lug 33 of the support frame. The top end of the piston rod one 36 is connected to the hydraulic rotating lug 38 of the upper heavy-duty crossbeam, and the top end of the piston rod two 37 is connected to the hydraulic rotating lug 38 of the lower heavy-duty crossbeam. Two independent hydraulic cylinders drive the lifting heavy-duty crossbeam 3 to rise and fall, thereby enabling independent adjustment of the traction height of the rope 101 at different positions on the heavy-duty flexible lightweight wing test piece 201. A hydraulically driven telescopic arm mechanism is formed by the support frame hydraulic rotating lug 33, hydraulic cylinder 34, and the crossbeam hydraulic rotating lug 38 on one side of the telescopic heavy-duty support frame 2. This mechanism hydraulically controls the extension of the upper heavy-duty crossbeam and the upper heavy-duty crossbeam to slide up and down along the height direction of the heavy-duty telescopic vertical beam 22. Similarly, another hydraulically driven telescopic arm mechanism is formed by the support frame hydraulic rotating lug 33, hydraulic cylinder 35, and the crossbeam hydraulic rotating lug 38 on the other side. This mechanism hydraulically controls the lower heavy-duty crossbeam to slide up and down along the height direction of the heavy-duty telescopic vertical beam 22. The upper and lower heavy-duty crossbeams are connected to the heavy-duty flexible lightweight wing test piece 201 via rope 101.

[0062] The aerodynamic equivalent loading of the heavy-load flexible lightweight wing test piece 201 is achieved through a liquid-infusion integrated loading device 6, such as... Figure 5As shown, the infusion-type integrated loading device 6 includes a pump-liquid integrator 62, multiple loading liquid bags 61, infusion lines 63 corresponding to each loading liquid bag 61, and a liquid bag force gauge 64. There is only one pump-liquid integrator 62, while multiple sets of loading liquid bags 61, infusion lines 63, and liquid bag force gauges 64 are provided. The specific number is determined according to the loading position. Each loading position is provided with one set of loading liquid bags 61, infusion lines 63, and liquid bag force gauges 64. Multiple liquid bag force gauges 64 are suspended at spanwise intervals on the lower wing surface of the heavy-duty flexible lightweight wing test piece 201. The position of the liquid bag force gauge 64 is the loading position. A loading liquid bag 61 is connected to the bottom of the liquid bag force gauge 64. The loading liquid bag 61 is connected to the pump-liquid integrator 62 through a corresponding infusion line 63. That is, each loading liquid bag 61 is connected to the pump-liquid integrator 62 through an independent infusion line 63. The load applied by the loading liquid bag 61 can be measured by the liquid bag force gauge 64. The pump-liquid integrator 62 is used to control the infusion rate and infusion direction of each infusion line 63, thereby individually controlling the infusion volume of each loading liquid bag 61, and thus controlling the applied load at a single loading liquid bag 61. The data monitoring terminal 5 is connected to each liquid bag force gauge 64 to monitor and record the real-time data of the liquid bag force gauge 64.

[0063] In order to achieve the hoisting of the loaded liquid bag 61, a reinforcing metal adhesive piece corresponding to the liquid bag force gauge 64 is bonded at intervals along the span of the lower wing surface of the heavy-duty flexible lightweight wing test piece 201. That is, a reinforcing metal adhesive piece is bonded at each loading position; the liquid bag force gauge 64 is connected to the corresponding reinforcing metal adhesive piece by a rope.

[0064] like Figure 4 As shown, the preload adjuster 4 connected between the pull ropes 101 includes a heavy-duty turnbuckle 41 and a pull rope force gauge 42. One end of the heavy-duty turnbuckle 41 is threadedly connected to one end of the pull rope force gauge 42, and the other end of the heavy-duty turnbuckle 41 is connected to the pull rope 101 attached to the pull rope anchor 32. The other end of the pull rope force gauge 42 is connected to the pull rope 101 attached to the upper wing surface of the heavy-duty flexible lightweight wing test piece 201. The total length of the preload adjuster 4 can be adjusted through the threaded connection between the heavy-duty turnbuckle 41 and the pull rope force gauge 42, thereby adjusting the preload of the pull rope 101. The data monitoring terminal 5 is connected to each pull rope force gauge 42 to monitor and record the real-time data of the pull rope force gauge 42. To facilitate the connection of the pull rope 101, a pull ring 43 is provided at the end of the heavy-duty turnbuckle 41 and the pull rope force gauge 42 that connects to the pull rope 101.

[0065] Since the stress on the tethering rope 101 of the heavy-load flexible lightweight wing test specimen 201 is directly affected by the height of the tethering post 32, and the other end of the rope 101 directly affects the stiffness of the tethering position of the heavy-load flexible lightweight wing test specimen 201, the measurement platform can be equipped with the ability to measure the static strength and instability boundary of the heavy-load flexible lightweight wing test specimen 201 under different stiffness conditions at different positions by freely controlling and changing the height of multiple heavy-load crossbeams 31.

[0066] The aforementioned measurement platform fine-tunes the preload of the pull rope 101 using a heavy-duty turnbuckle sleeve 41, and monitors the preload of the pull rope 101 in real time using a pull rope force gauge 42 connected to it. This achieves the purpose of testing the stiffness and instability boundary of the heavy-duty flexible lightweight wing test specimen 201 under different preloads. Simultaneously, the measurement platform, through the control of the pump-liquid integrator 62, can precisely control different loading levels and progressive loading at different locations on the heavy-duty flexible lightweight wing test specimen 201, achieving equivalent fine loading of aerodynamic load distribution in different areas of the heavy-duty flexible lightweight wing test specimen 201 under different working conditions, greatly improving loading accuracy. Furthermore, the infusion bag loading method can significantly increase the upper limit of loading, meeting the static strength and stiffness limit loading requirements of the heavy-duty flexible lightweight wing test specimen 201.

[0067] The data monitoring terminal 5 is used to monitor the real-time data of each rope force gauge 42, each liquid bag force gauge 64 of the infusion-type integrated loading device 6, and each displacement gauge 601 under the heavy-duty flexible lightweight wing test piece 201 under different bending and torsion conditions, and to record and store the data.

[0068] In order to improve the testing accuracy, the above-mentioned measurement platform can also be fixedly installed on a ground test platform during the testing process.

[0069] The specific working principle of the above measurement platform is as follows:

[0070] First, the wing clamping fixture mold 11, made according to the wing root airfoil of the heavy-load flexible lightweight wing test piece 201 to be tested, is positioned and adjusted. After the position adjustment is completed, the wing clamping fixture mold 11 is locked onto the mold fixture table 16. According to the test conditions, the upper variable wing root mold 12 and the lower variable wing root mold 13 are flipped up and down to complete the clamping and locking at the wing root. Figure 6 and Figure 7 As shown.

[0071] Then, as Figure 8 and Figure 9As shown, the heavy-duty flexible lightweight wing test piece 201 is inflated through an external inflation device and inflation pipeline 202 until the target pressure is reached and the pressure holding function is activated. The heavy-duty telescopic vertical beam 22 of the telescopic heavy-duty support frame 2 is adjusted to a predetermined height and locked by a heavy-duty winch. The traction height of the pull rope 101 at different positions of the heavy-duty flexible lightweight wing test piece 201 is independently adjusted by two independent hydraulically driven lifting heavy-duty crossbeams 3. The pull rope anchor post 32 is used to anchor the pull rope 101. The other end of the pull rope 101 is anchored to the heavy-duty turnbuckle 41 of the pretension force adjuster 4. The other end of the pull rope force gauge 42, which is fixedly connected to the heavy-duty turnbuckle 41, is anchored to another pull rope 101. The other end of this pull rope 101 is anchored to the handle on the upper wing surface of the heavy-duty flexible lightweight wing test piece 201 to complete the fixed traction of the entire heavy-duty flexible lightweight wing test piece 201. The preload of the pull rope 101 is finely adjusted by the spiral of the heavy-duty turnbuckle 41 and the pull rope force gauge 42, and the preload of the pull rope 101 is monitored in real time by the pull rope force gauge 42 which is threadedly connected to the heavy-duty turnbuckle 41. During this process, the preload of the pull rope 101 is monitored in real time by the data monitoring terminal 5.

[0072] Finally, as Figure 10 As shown, the heavy-load flexible lightweight wing test specimen 201 is loaded by controlling the pump integrator 62 of the infusion-type integrated loading device 6 to infuse liquid into each loading liquid bag 61 until the predetermined equivalent load is reached. The real-time data of the liquid bag force gauge 64 and displacement gauge 601 are measured and recorded. The stiffness and instability boundary of the heavy-load flexible lightweight wing test specimen 201 are finally measured by adopting a step-by-step loading strategy.

[0073] Obviously, those skilled in the art can make various modifications and variations to the embodiments of the present invention without departing from the spirit and scope of the invention. Therefore, if these modifications and variations fall within the scope of the claims of the present invention and their equivalents, the present invention also intends to include these modifications and variations.

[0074] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A platform for measuring the bending and torsional stiffness of a heavy-duty, lightweight airfoil with a high aspect ratio, characterized in that, It includes a variable wing root wing clamping platform (1), a telescopic heavy-duty support frame (2), a lifting heavy-duty crossbeam (3), a preload adjuster (4), a data monitoring terminal (5), an infusion-type integrated loading device (6), and a displacement meter (601). The variable wing root wing clamping platform and the telescopic heavy-duty support frame are both fixedly installed on the ground, with the two telescopic heavy-duty support frames located on both sides of the variable wing root wing clamping platform. The variable wing root wing clamping platform is used to clamp and fix the wing root of the heavy-load flexible lightweight wing test piece, so that the heavy-load flexible lightweight wing test piece forms a cantilever beam structure. The lifting heavy-duty crossbeam is located on top of the variable wing root wing clamping platform and can be slidably installed on the two telescopic heavy-duty support frames in a vertical direction. The two ends of the preload adjuster are respectively connected between the heavy-duty crossbeam and the wing surface of the heavy-duty flexible lightweight wing test piece by pull ropes, and are used to adjust the preload of the pull ropes; The infusion-type integrated loading device is used to apply aerodynamic equivalent loading to the heavy-load flexible lightweight wing test piece through multiple loading liquid bags distributed along the spanwise direction of the heavy-load flexible lightweight wing test piece, so as to simulate different bending and torsional conditions. The displacement gauge is installed on the ground directly below the heavy-load flexible lightweight wing test specimen and is used to measure the displacement of the heavy-load flexible lightweight wing test specimen before and after loading. The data monitoring terminal is connected to the infusion-type integrated loading device, the preload adjuster, and the displacement gauge, and is used to monitor and store the preload of each pull rope, the loading load of each loading liquid bag, and the real-time data of each displacement gauge. The variable wing root wing clamping platform includes a mold tooling platform (16) made of high-strength aluminum alloy, a wing clamping tooling mold (11), an upper variable wing root mold (12), and a lower variable wing root mold (13). The mold tooling table is fixedly installed on the ground and located between the two telescopic heavy-duty support frames; The wing clamping tooling mold is slidably installed on the mold tooling table and is provided with a through hole (14) extending in the horizontal direction and perpendicular to the arrangement direction of the two telescopic heavy-duty support frames; the through hole is matched with the airfoil shape at the wing root of the heavy-duty flexible lightweight wing test piece and is used to accommodate the wing root clamping section of the inflated heavy-duty flexible lightweight wing test piece. The upper variable wing root mold and the lower variable wing root mold are vertically opposite each other on the upper and lower sides of the through hole, and are rotatably mounted on the wing clamping fixture mold via hinges; after the upper variable wing root mold and the lower variable wing root mold are connected and locked together, they form a complete wing clamping mold for clamping heavy-load flexible lightweight wing test pieces; the clamping airfoil contour edges of the upper variable wing root mold and the lower variable wing root mold are designed with large rounded chamfers, which can effectively reduce the risk of cutting the flexible lightweight wing when the wing root of the heavy-load flexible lightweight wing test piece becomes unstable, and improve the accuracy of the instability test; The top surface of the wing clamping tooling mold is also provided with an opening slot that communicates with the through hole. The opening slot facilitates the exposure of the air nozzle of the heavy-duty flexible lightweight wing test piece and the connection of the inflation pipeline. The infusion-type integrated loading device includes a pump-liquid integrator (62), multiple loading liquid bags (61), an infusion pipeline (63) corresponding to each loading liquid bag, and a liquid bag force gauge (64). Multiple liquid bag force gauges are suspended at spanwise intervals on the lower wing surface of the heavy-duty flexible lightweight wing test specimen. The bottom end of the liquid bag force gauge is connected to a loading liquid bag; The loading fluid bag is connected to the pump-liquid integrator via a corresponding infusion pipeline; The pump-liquid integrator is used to control the infusion rate and direction of each infusion line, thereby individually controlling the infusion volume of each loading fluid bag; The data monitoring terminal is connected to each liquid bag force gauge and is used to monitor and record the real-time data of the liquid bag force gauge. Reinforcing metal bonding pieces, corresponding to the liquid bag force gauges, are bonded at spanwise intervals on the lower wing surface of the heavy-duty flexible lightweight wing test piece; the liquid bag force gauges are connected to the corresponding reinforcing metal bonding pieces by ropes. The telescopic heavy-duty support frame includes a support frame base (21), a heavy-duty telescopic vertical beam (22), and a heavy-duty horizontal beam slide rail (23); the support frame base is fixed to the ground and has a through square hole along the height direction; the heavy-duty telescopic vertical beam is installed in the square hole; the support frame base has a built-in heavy-duty winch, which is used to control the telescopic extension and retraction of the heavy-duty telescopic vertical beam along the height direction; the heavy-duty horizontal beam slide rail is fixedly installed on the side of the heavy-duty telescopic vertical beam facing the mold tooling table; the lifting heavy-duty horizontal beam includes two heavy-duty horizontal beams. A beam (31) and a hydraulic cylinder corresponding to each of the heavy-duty crossbeams; two heavy-duty crossbeams are spaced apart in the vertical direction; the heavy-duty crossbeam spans between the two telescopic heavy-duty support frames, and its end slides with the slide rails of the two heavy-duty crossbeams; the hydraulic cylinder is installed between the heavy-duty crossbeam and the support frame base, and is used to drive the corresponding heavy-duty crossbeam to slide in the vertical direction along the slide rail of the heavy-duty crossbeam; the middle section of the heavy-duty crossbeam forms a rope tethering post (32), which is used to tether the other end of the rope connecting the preload adjuster.

2. The high aspect ratio heavy-duty lightweight wing bending and torsional stiffness measurement platform as described in claim 1, characterized in that, The top surface of the mold tooling table is provided with a sliding groove; the lower edge of the wing clamping tooling mold is provided with a sliding tenon; the sliding tenon is slidably installed in the sliding groove, so that the mold tooling table can slide along the spanwise direction of the flexible lightweight wing; The mold tooling table has a scale line (15) on one side of the sliding slot on its top surface. The scale line is used to measure the sliding distance of the wing clamping tooling mold relative to the mold tooling table.

3. The high aspect ratio heavy-duty lightweight airfoil bending and torsional stiffness measurement platform as described in claim 1, characterized in that, Both ends of the heavy-duty crossbeam are provided with an extension section that is suspended on one side of the heavy-duty telescopic vertical beam, and the outer side of the extension section is welded with a hydraulic rotating lug of the crossbeam. The top surface of the support frame base is welded with a hydraulic rotating lug for the support frame; the hydraulic rotating lug for the support frame and the hydraulic rotating lug for the crossbeam are located on the same side of the heavy-duty telescopic vertical beam. The bottom end of the hydraulic cylinder is rotatably mounted on the hydraulic rotating lug of the support frame; the piston rod of the hydraulic cylinder is rotatably mounted on the hydraulic rotating lug of the crossbeam. The lifting heavy-duty crossbeam is raised and lowered by two independent hydraulic cylinders, thereby enabling independent adjustment of the traction height of the ropes at different positions on the heavy-duty flexible lightweight wing test specimen.

4. The high aspect ratio heavy-duty lightweight airfoil bending and torsional stiffness measurement platform as described in any one of claims 1-3, characterized in that, The preload adjuster includes a heavy-duty turnbuckle sleeve and a pull rope force gauge; The heavy-duty turnbuckle sleeve is threaded to one end of the pull rope force gauge, and the other end of both the heavy-duty turnbuckle sleeve and the pull rope force gauge are connected to a pull rope. The preload of the pull rope is adjusted by the threaded connection between the heavy-duty turnbuckle and the pull rope force gauge; The data monitoring terminal is connected to each pull rope force gauge and is used to monitor and record the real-time data of the pull rope force gauge.

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