A variable stiffness lightweight wing static strength testing device

Abstract

The present application belongs to the technical field of flexible body aircraft, and particularly relates to a variable stiffness lightweight wing static strength testing device. The testing device comprises a wing clamping tool, a mold installation platform, a rope height adjusting device, a wing stiffness adjuster, an inflation device, a data monitoring and collecting device, a rope, a loading weight and a displacement measuring device. The rope height adjusting device is located directly above the wing clamping tool. The wing stiffness adjuster is connected with the rope height adjusting device and the flexible lightweight wing through the rope. The data monitoring and collecting device is used for monitoring the pre-tightening force of the rope to quantitatively control the stiffness adjustment of the wing stiffness adjuster to the flexible lightweight wing. The displacement measuring device is used for collecting the displacement of different measuring points of the flexible lightweight wing. The above testing device realizes the direct measurement of the load bearing performance and static strength of the variable stiffness flexible lightweight wing, and significantly improves the reliability and flexibility of the static strength and stiffness testing of the flexible lightweight wing.

Description

Technical Field

[0001] This invention belongs to the field of flexible body aircraft technology, specifically relating to a static strength testing device for a variable stiffness lightweight wing. Background Technology

[0002] Flexible lightweight wings are widely used in small and medium-sized aircraft such as biomimetic aircraft and morphing aircraft due to their significant advantages such as light weight, small storage space, and simple structure. However, the material and structural characteristics of flexible lightweight wings mean that they have insufficient stiffness compared to rigid wings. How to accurately and reliably obtain the stiffness and static strength of flexible wings has become a challenge in the design of flexible lightweight wing aircraft.

[0003] A wing static strength testing device is a type of testing device that can obtain the structural response of an aircraft under extreme loads that it may encounter in the air through simulated loading. Traditional wing static strength testing devices can only realize loading in the form of flat or end-suspended weights. They cannot directly simulate the distributed loading of aerodynamic loads on flexible lightweight wings with stiffness enhanced by struts and cables, nor can they conduct static strength and stiffness tests on lightweight inflatable wings under variable stiffness conditions. Their application limitations are prominent and they can no longer meet the testing requirements for the load-bearing performance of new flexible lightweight wings.

[0004] Therefore, it is necessary to develop a flexible lightweight wing static strength testing device with a wide range of applications and high testing accuracy to meet the testing requirements of the special performance of flexible lightweight wings under complex conditions. Summary of the Invention

[0005] To address the problems of existing technologies, this invention provides a static strength testing device for a variable stiffness lightweight airfoil.

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

[0007] This invention provides a static strength testing device for a variable stiffness lightweight wing. The testing device includes a wing clamping fixture, a molding platform, a rope height adjustment device, a wing stiffness adjuster, an inflation device, a data monitoring and acquisition device, a loading counterweight, and a displacement measuring device.

[0008] The molding platform and the rope height adjustment device are both fixedly installed on the ground. The wing clamping fixture is position-adjustable and installed on the top of the molding platform for clamping the wing root of the flexible lightweight wing test piece. The two ends of the wing stiffness adjuster are connected to the rope height adjustment device and the flexible lightweight wing test piece via ropes, respectively, for adjusting the stiffness of the flexible lightweight wing test piece by changing the tension of the ropes. The rope height adjustment device is used to adjust the height of one end of the rope. The inflation device is used for inflating and stabilizing the pressure of the flexible lightweight wing test piece. The loading counterweight is used to load the flexible lightweight wing test piece. The displacement measuring device is positioned directly below the flexible lightweight wing test piece for measuring the displacement at different positions of the flexible lightweight wing test piece. The data monitoring and acquisition device is connected to the wing stiffness adjuster and the displacement measuring device for real-time monitoring and recording of the rope tension and the displacement at different positions of the flexible lightweight wing test piece, thereby calculating the stiffness of the flexible lightweight wing test piece.

[0009] Furthermore, the wing clamping fixture includes a wing clamping mold, a mold holder, and a holder fixing knob;

[0010] Two opposing mold holders clamp the wing clamping mold in the middle and fix it to the mold assembly platform by the clamping holder fixing knob;

[0011] The wing clamping mold is provided with a molded through hole that matches the airfoil shape at the wing root of the flexible lightweight wing test piece; the molded through hole extends along the spanwise direction of the flexible lightweight wing test piece and is used to clamp the wing root of the flexible lightweight wing test piece.

[0012] The top surface of the wing clamping mold is provided with a through groove for accommodating the air nozzle of the flexible lightweight wing test piece; the air nozzle is used to connect to the inflation device.

[0013] Furthermore, the mold holder is a rectangular structure made of high-strength alloy steel, and has a groove on the side facing the wing where the mold is held.

[0014] The wing clamping mold is provided with fixing latches on both sides facing the mold holder;

[0015] The fixed tenon is fitted into the groove in a matching shape, and the longitudinal position of the wing clamping mold is adjusted by sliding the fixed tenon along the groove.

[0016] Furthermore, the molding platform includes a wing clamping fixture base;

[0017] The wing clamping fixture base is a thick-walled alloy steel structure, which is fixed to the ground by high-strength bolts. The top surface is provided with a clamping device sliding groove and a displacement scale.

[0018] The bottom of the mold holder is provided with sliding latches that correspond one-to-one with the sliding grooves of the holder;

[0019] The sliding tenon is slidably installed in the corresponding clamp sliding groove;

[0020] The mold holder achieves lateral position adjustment of the wing clamping mold by sliding the sliding tenon along the sliding groove of the holder;

[0021] The displacement scale is used to laterally position the mold holder when the sliding latch slides along the sliding groove of the holder, so as to accurately position the wing clamping mold held by the mold holder.

[0022] Furthermore, the rope height adjustment device includes a door beam support platform, a main crossbeam, and a main crossbeam fixing knob;

[0023] The bottom end of the portal beam support platform is located on both sides of the molding platform and fixed to the ground;

[0024] The two ends of the main crossbeam are slidably engaged with the portal beam support platform, and can only slide vertically along the portal beam support platform; a tie post is formed in the middle of the main crossbeam, and the tie post is used to tie one end of the pull rope.

[0025] The main crossbeam fixing knobs are installed at both ends of the main crossbeam to lock the main crossbeam to the door beam support platform, so that there is no slippage between the main crossbeam and the door beam support platform.

[0026] Furthermore, the portal beam support platform includes a main support vertical beam, a main beam support triangular frame, a ground stabilizing frame, and a main crossbeam sliding guide rail;

[0027] The main support vertical beams are provided on both sides of the molding platform; the main support vertical beams are vertically placed square thick-walled beam structures and are fixed to the ground by tooling bolts;

[0028] The main beam support triangle is vertically installed and welded to the main support vertical beam to enhance the longitudinal stability of the main support vertical beam.

[0029] The ground stabilizing frame is horizontally set on the ground and welded to the bottom surface of the main beam support triangle to enhance the lateral stability of the main support vertical beam.

[0030] The main crossbeam sliding guide rail is vertically arranged and fixedly installed on the inner side of the main support vertical beam facing the molding platform;

[0031] The main crossbeam is slidably engaged with the main crossbeam sliding guide rail through the slots at both ends, so that it can only slide along the main crossbeam sliding guide rail in the vertical direction.

[0032] Furthermore, the main crossbeam sliding guide rail is an I-beam shaped structure; the main support vertical beam has weight-reducing holes evenly distributed along the vertical direction.

[0033] Furthermore, the wing stiffness adjuster includes two tie lugs, a sleeve bearing, an internally threaded screw-in sleeve, an externally threaded screw-in post, and a pull rope force gauge;

[0034] The tethering lug includes a cylinder and a tethering ring; the tethering ring is used to connect and fasten the pull rope; one end of the cylinder is fixedly connected to the tethering ring, and the other end is equipped with a sleeve bearing;

[0035] A pull rope is connected between the tethering ring of one of the tethering ears and the tethering post, and another pull rope is connected between the tethering ring of the other tethering ear and the flexible lightweight wing test piece.

[0036] One sleeve bearing is externally connected to the internally threaded sleeve, and the other sleeve bearing is externally connected to the pull rope force gauge. The sleeve bearings enable both the internally threaded sleeve and the pull rope force gauge to rotate freely around the end lug.

[0037] One end of the external thread screw-in column is fixedly connected to the pull rope force gauge, and the other end is threadedly connected to the internal thread screw-in sleeve. The preload of the pull rope is adjusted by the helical engagement of the external thread screw-in column and the internal thread screw-in sleeve.

[0038] The pull rope force gauge is used to measure the tension of the pull rope and transmit the data to the data monitoring and acquisition device in real time.

[0039] Furthermore, the inflation device includes an air storage device, a pressure stabilizing device, a pressure display, and an inflation pipeline connected in sequence;

[0040] The gas storage device is inflated and stores high-pressure gas using an air compressor; the gas storage device is connected to the pressure stabilizing device via an inflation valve; the pressure stabilizing device is used to achieve constant pressure output of the high-pressure gas; the pressure display is used to display the gas pressure; the inflation pipeline inputs the constant-pressure high-pressure gas into the flexible lightweight wing test piece through the air nozzle.

[0041] Furthermore, the data monitoring and acquisition device includes a data monitoring display screen and a data processor;

[0042] The data processor is connected to the displacement measuring device, the pull rope force gauge and the data monitoring display signal, and is used to monitor and record the tension of the pull rope and the displacement values ​​at different positions of the flexible lightweight wing test piece in real time.

[0043] The loading counterweight is a flat sandbag;

[0044] The displacement measuring device is a laser displacement sensor.

[0045] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0046] 1. The variable stiffness lightweight wing static strength testing device of the present invention overcomes the shortcomings of traditional flexible lightweight wing static strength testing devices that cannot test complex airfoils. It can carry out static strength tests on flexible lightweight wings with strut and rope stiffness reinforcement methods. It realizes direct testing of the load-bearing performance of variable stiffness flexible lightweight wings through wing stiffness adjuster and rope height adjustment device, and can also be extended to the field of inflatable wing stiffness testing.

[0047] 2. The wing stiffness adjuster of the variable stiffness lightweight wing static strength testing device of the present invention has a simple structure consisting of a sleeve bearing, an internally threaded screw-in sleeve, and an externally threaded screw-in column. It can realize the static strength measurement of flexible lightweight wings with different stiffness by manually adjusting the preload of the pull rope. The pull rope preload is visualized and precisely adjusted by the pull rope force gauge connected to the pull rope and the data monitoring and acquisition device, which significantly improves the reliability and flexibility of the static strength and stiffness testing of flexible lightweight wings.

[0048] 3. The variable stiffness lightweight wing static strength testing device of the present invention can flexibly adjust the height of the pull rope by means of the pull rope height adjustment device. For the first time, it has the ability to test the static strength and instability boundary of flexible lightweight wing test pieces under different pull rope heights, providing a basis for the design of strut pull rope system for stiffness-enhanced flexible lightweight wing structures.

[0049] 4. In the static strength testing device for variable stiffness lightweight wings of the present invention, the wing clamping fixture adopts a modular design with replaceable wing clamping molds, and the wing clamping mold, mold holder and mold mounting platform are designed separately. Compared with traditional testing devices, the testing device of the present invention can test flexible lightweight wings, lightweight inflatable wing structures and various rigid wings, and its flexibility and applicability are greatly improved. The design of the displacement scale increases the accuracy of the position adjustment of the clamping wing mold, so that the test results are more consistent with the actual flight state of the flexible lightweight wing aircraft.

[0050] In summary, the variable stiffness lightweight wing static strength testing device of the present invention can be widely promoted and applied in the field of flexible body aircraft technology. Attached Figure Description

[0051] Figure 1 This is an overall layout diagram of the static strength testing device for a variable stiffness lightweight wing according to the present invention;

[0052] Figure 2This is a schematic diagram of the molded platform of the static strength testing device for the variable stiffness lightweight wing of the present invention;

[0053] Figure 3 This is a schematic diagram of the draw rope height adjustment device of the static strength testing device for a variable stiffness lightweight wing of the present invention;

[0054] Figure 4 This is a schematic diagram of the wing stiffness adjuster of the variable stiffness lightweight wing static strength testing device of the present invention;

[0055] Figure 5-8 This is a schematic diagram of the testing process of the variable stiffness lightweight airfoil static strength testing device of the present invention.

[0056] Figure label:

[0057] 1-Wing clamping fixture; 2-Mold assembly platform; 3-Gantry support platform; 4-Pull rope height adjustment device; 5-Wing stiffness adjuster; 6-Inflation device; 7-Data monitoring and acquisition device; 11-Wing clamping mold; 12-Fixing latch; 13-Through groove; 14-Mold holder; 15-Holder fixing knob; 21-Holder sliding groove; 22-Displacement scale; 23-Wing clamping fixture base; 31-Main support vertical beam; 32-Main beam support tripod; 33-Ground stabilizing frame; 34-Weight reduction hole ; 35-Main crossbeam sliding guide rail; 41-Main crossbeam; 42-Tethering post; 43-Main crossbeam fixing knob; 51-Tethering lug; 52-Sleeve bearing; 53-Internal threaded sleeve; 54-External threaded post; 55-Stretch rope force gauge; 61-Air storage device; 62-Pressure stabilizing device; 63-Pressure display; 64-Inflation pipeline; 71-Data monitoring display screen; 72-Data processor; 101-Flexible lightweight wing test piece; 201-Stretch rope; 301-Loading counterweight; 501-Displacement measuring device. Detailed Implementation

[0058] 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.

[0059] 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.

[0060] like Figure 1 As shown, this embodiment of the invention provides a static strength testing device for a variable stiffness lightweight wing. The testing device includes a wing clamping fixture 1, a molding platform 2, a rope height adjustment device 4, a wing stiffness adjuster 5, an inflation device 6, a data monitoring and acquisition device 7, a loading counterweight 301, and a displacement measuring device 501. The bottom ends of the molding platform 2 and the rope height adjustment device 4 are both fixedly installed on the ground, and the ground must be a flat ground or a testing platform.

[0061] The wing clamping fixture 1 is position-adjustable and mounted on top of the molding platform 2 to clamp the wing root of the flexible lightweight wing test piece 101 to fix the position and orientation of the flexible lightweight wing test piece 101. For example... Figure 2As shown, the wing clamping fixture 1 includes a wing clamping mold 11, mold holders 14, and holder fixing knobs 15. Two mold holders 14 are arranged opposite each other on both sides of the wing clamping mold 11, clamping the wing clamping mold 11 in the middle. The holders 14 are fixed to the molding platform 2 by the holder fixing knobs 15, thereby fixing the wing clamping mold 11 to the molding platform 2 as well. The wing clamping mold 11 has a square structure and is provided with a molding through hole that matches the airfoil shape at the wing root of the flexible lightweight wing test piece 101. The molding through hole extends along the spanwise direction of the flexible lightweight wing test piece 101 and is used to clamp the wing root of the flexible lightweight wing test piece 101. The wing clamping mold 11 can be manufactured and replaced according to the airfoil shape of the flexible lightweight wing test piece 101 being tested, and it has good adaptability, especially for flexible lightweight wing test pieces 101 with heterogeneous shapes. The top surface of the wing clamping mold 11 has multiple through slots 13; the through slots 13 communicate with the mold mounting through holes and are used to accommodate the air nozzles of the flexible lightweight wing test piece 101. The air nozzles can pass through the through slots 13 and connect to the inflation device 6. The air nozzles are used to connect to the inflation device 6, and the inflation device 6 inflates the flexible lightweight wing test piece 101. The mold holder 14 is a rectangular structure made of high-strength alloy steel and has a groove on one side facing the wing clamping mold 11. The wing clamping mold 11 has fixing tenons 12 on both sides facing the mold holder 14; the fixing tenons 12 are fitted into the grooves in a matching shape, and the wing clamping mold 11 can be adjusted in the longitudinal direction (the spanwise direction of the flexible lightweight wing test piece 101) by sliding the fixing tenons 12 along the grooves. The molding platform 2 includes a wing clamping fixture base 23; the wing clamping fixture base 23 is a thick-walled alloy steel structure, which is fixed to the ground by high-strength bolts, and has a clamping device sliding groove 21 and a displacement scale 22 on its top surface. The bottom of the mold holder 14 is provided with sliding latches corresponding to the sliding grooves 21 of the holder. In this embodiment, there are two sliding grooves 21 of the holder and two sliding latches corresponding to the sliding grooves 21 of the holder. The sliding latches are slidably installed in the corresponding sliding grooves 21 of the holder. The mold holder 14 adjusts the position of the wing clamping mold 11 in the lateral direction (chord direction of the flexible lightweight wing test piece 101) by sliding the sliding latches along the sliding grooves 21 of the holder. The displacement scale 22 is used to laterally position the mold holder 14 when the sliding latches slide along the sliding grooves 21 of the holder, so as to accurately position the wing clamping mold 11 held by the mold holder 14.

[0062] The two ends of the wing stiffness adjuster 5 are connected between the rope height adjustment device 4 and the flexible lightweight wing test piece 101 via pull ropes 201, respectively, to adjust the stiffness of the flexible lightweight wing test piece 101 by changing the tension of the pull ropes 201. In this embodiment, two wing stiffness adjusters 5 are used as an example. One wing stiffness adjuster 5 is connected between the rope height adjustment device 4 and the wing center of the flexible lightweight wing test piece 101 via pull ropes 201 at both ends, and the other wing stiffness adjuster 5 is connected between the rope height adjustment device 4 and the wingtip of the flexible lightweight wing test piece 101 via pull ropes 201 at both ends. Figure 4 As shown, the wing stiffness adjuster 5 includes two tether lugs 51, a sleeve bearing 52, an internally threaded screw-in sleeve 53, an externally threaded screw-in post 54, and a pull rope force gauge 55. A tether lug 51 is installed at each end of the wing stiffness adjuster 5. Each tether lug 51 includes a cylinder and a tether ring; the tether ring is an annular component used to connect and tighten one end of the pull rope 201. One end of the cylinder is fixedly connected to the tether ring, and the other end is equipped with a sleeve bearing 52. In each of the two tethering lugs 51 of the wing stiffness adjuster 5, a pull rope 201 is connected between the tethering ring of one tethering lug 51 and the tethering post 42, and another pull rope 201 is connected between the tethering ring of the other tethering lug 51 and the flexible lightweight wing test piece 101, thereby realizing the connection between the pull rope height adjustment device 4 and the flexible lightweight wing test piece 101; one sleeve bearing 52 is externally connected to the internally threaded sleeve 53, and the other sleeve bearing 52 is externally connected to the pull rope force gauge 55, so that the internally threaded sleeve 53 and the pull rope force gauge 55 can both rotate freely around the end tethering lug 51 through the sleeve bearing 52. One end of the external thread screw-in post 54 is fixedly connected to the pull rope force gauge 55, and the other end is threadedly connected to the internal thread screw-in sleeve 53. The preload of the pull rope 201 is adjusted by the helical engagement of the external thread screw-in post 54 and the internal thread screw-in sleeve 53. The pull rope force gauge 55 is used to measure the tension of the pull rope 201 and transmit it to the data monitoring and acquisition device 7 in real time.

[0063] When the tether 51 is tightened, the internally threaded sleeve 53 can only rotate freely around the tether 51 via the sleeve bearing 52. The internal thread of the internally threaded sleeve 53 engages with the external thread of the externally threaded post 54. One end of the externally threaded post 54 can be screwed into the internally threaded sleeve 53, and a pull rope force gauge 55 is welded to the other end of the externally threaded post 54. The other end of the pull rope force gauge 55 is connected to a tether 51 via the sleeve bearing 52 for tightening the pull rope 201 connected to the flexible lightweight wing test piece 101. When both tethers 51 are tightened, the pull rope force gauge 55 can measure the tension or preload of the pull rope 201 and transmit it in real time to the data monitoring display 71 of the data monitoring and acquisition device 7 connected to it. When it is necessary to adjust the preload of the pull rope 201 to adjust the stiffness of the flexible lightweight wing test piece 101, it is only necessary to manually limit the displacement of the external thread screw-in post 54, rotate the internal thread screw-in sleeve 53, and adjust the screw-in depth of the external thread screw-in post 54 in the internal thread screw-in sleeve 53, thereby changing the length of the pull rope 201.

[0064] The rope height adjustment device 4 is used to adjust the height of one end of the rope 201, thereby adjusting the angle between the rope 201 and the flexible lightweight wing test piece 101. Figure 3As shown, the rope height adjustment device 4 includes a portal beam support platform 3, a main crossbeam 41, and a main crossbeam fixing knob 43. The bottom end of the portal beam support platform 3 is located on both sides of the molding platform 2 and fixed to the ground, providing support for the main crossbeam 41. Both ends of the main crossbeam 41 are slidably engaged with the portal beam support platform 3 and can only slide vertically along the portal beam support platform 3. The freedom of the main crossbeam 41 in other directions is restricted, thereby adjusting the height of one end of the rope 201. A tie post 42 is formed in the middle of the main crossbeam 41, which is used to tie one end of the rope 201. The main crossbeam fixing knob 43 is installed at both ends of the main crossbeam 41 and is used to lock the main crossbeam 41 to the portal beam support platform 3 after the height adjustment of the main crossbeam 41 is completed, so that there is no slippage between the main crossbeam 41 and the portal beam support platform 3. The portal beam support platform 3 includes a main support vertical beam 31, a main beam support triangle 32, a ground stabilizing frame 33, and a main crossbeam sliding guide rail 35. Main support vertical beams 31 are installed on both sides of the molding platform 2. The main support vertical beam 31 is a vertically placed square thick-walled beam structure, fixed to the ground by tooling bolts. The main beam support triangle 32 is vertically installed and welded to the main support vertical beam 31 to enhance the longitudinal (spanwise) stability of the main support vertical beam 31. The ground stabilizing frame 33 is horizontally installed on the ground and welded to the bottom surface of the main beam support triangle 32 to enhance the lateral (chordwise) stability of the main support vertical beam 31. The main crossbeam sliding guide rail 35 is vertically arranged and fixedly installed on the inner side of the main support vertical beam 31 facing the molding platform 2; the main crossbeam 41 slides along the main crossbeam sliding guide rail 35 through the slots at both ends, so that it can only slide along the main crossbeam sliding guide rail 35, that is, slide in the vertical direction. The main crossbeam sliding guide rail 35 is an I-beam shaped structure; the main support vertical beam 31 has weight-reducing holes 34 evenly distributed in the vertical direction for structural weight reduction.

[0065] Inflation device 6 is used for inflating and stabilizing the pressure of the flexible lightweight wing test piece 101; such as Figure 5 As shown, the inflation device 6 includes a gas storage device 61, a pressure stabilizing device 62, a pressure display 63, and an inflation pipeline 64 connected in sequence. The gas storage device 61 is inflated by an air compressor and stores high-pressure gas. The gas storage device 61 is connected to the pressure stabilizing device through an inflation valve. The pressure stabilizing device 62 is used to achieve constant pressure output of high-pressure gas. The pressure display 63 is used to display the gas pressure. The inflation pipeline 64 inputs the constant-pressure high-pressure gas into the flexible lightweight wing test piece 101 through an air nozzle.

[0066] The loading counterweight 301 is used to load the flexible lightweight wing test piece 101; the loading counterweight 301 is a flat sandbag or other form of counterweight.

[0067] Multiple displacement measuring devices 501 are arranged directly below the flexible lightweight wing test piece 101 to measure the displacement at different positions of the flexible lightweight wing test piece 101, thereby calculating the stiffness of the flexible lightweight wing test piece 101; the displacement measuring device 501 is a laser displacement sensor.

[0068] The data monitoring and acquisition device 7 is connected to the wing stiffness adjuster 5 and the displacement measuring device 501, and is used to monitor and record the tension of the tension rope 201 and the displacement of the flexible lightweight wing test piece 101 at different positions in real time, thereby calculating the stiffness of the flexible lightweight wing test piece 101. Figure 4 As shown, the data monitoring and acquisition device 7 includes a data monitoring display 71 and a data processor 72; the data processor 72 is connected to the displacement measuring device 501, the pull rope force gauge 55 and the data monitoring display 71, and is used to monitor and record the tension of the pull rope 201 and the displacement values ​​of the flexible lightweight wing test piece 101 at different positions in real time.

[0069] like Figure 5 , Figure 6 , Figure 7 and Figure 8 As shown, the specific working principle of the above-mentioned testing device is as follows:

[0070] First, a wing clamping mold 11 is made according to the airfoil of the flexible lightweight wing test piece 101. The position of the wing clamping mold 11 is adjusted by the mold clamp 14 and tightened by the clamp fixing knob 15. The wing root clamping part of the uninflated flexible lightweight wing test piece 101 is placed into the wing clamping mold 11 and inflated using the inflation device 6. The high-pressure gas generated by the air compressor is pumped into the flexible lightweight wing test piece 101 through the air storage device 61, the pressure stabilizing device 62, the pressure display 63 and the inflation pipeline 64. The air pressure is observed through the pressure display 63. After inflation reaches the target pressure, inflation is stopped and the pressure is stabilized.

[0071] Then, adjust the height of the main beam 41 of the pull rope height adjustment device 4, and lock the height using the main beam fixing knob 43. Tie one end of the pull rope 201 to the tethering post 42 and the other end to the tethering lug 51 of the wing stiffness adjuster 5. Tie one pull rope 201 to the tethering lug 51 at one end of the pull rope force gauge 55. Tie the other end of the pull rope 201 to the handle of the flexible lightweight wing test piece 101. Use the same method to tie and install multiple pull ropes 201 onto the flexible lightweight wing test piece 101. Each pull rope 201 is equipped with a pull rope height adjustment device 4. Obtain the real-time preload of the pull rope 201 through the pull rope force gauge 55 and the data monitoring and acquisition device 7 connected to it. Adjust the preload of the pull rope 201 by adjusting the screw thread of the internal threaded sleeve 53 until the preload target of the test condition is reached. The flexible lightweight wing test piece 101 is loaded with a counterweight 301. After loading, the tension data of the pull rope 201 and the displacement data of the displacement measuring device 501 are read and recorded. The static strength and stiffness results of the flexible lightweight wing test piece 101 are obtained by conversion calculation formula.

[0072] 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.

[0073] 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 static strength testing device for a variable stiffness lightweight airfoil, characterized in that, It includes a wing clamping fixture (1), a molding platform (2), a rope height adjustment device (4), a wing stiffness adjuster (5), an inflation device (6), a data monitoring and acquisition device (7), a loading counterweight (301), and a displacement measuring device (501); The molding platform and the rope height adjustment device are both fixedly installed on the ground; the wing clamping fixture is position-adjustable and installed on the top of the molding platform for clamping the wing root of the flexible lightweight wing test piece; the two ends of the wing stiffness adjuster are respectively connected between the rope height adjustment device and the flexible lightweight wing test piece via ropes, for adjusting the stiffness of the flexible lightweight wing test piece by changing the tension of the ropes; the rope height adjustment device is used to adjust the height of one end of the rope; the inflation device is used for inflating and stabilizing the pressure of the flexible lightweight wing test piece; the loading counterweight is used to load the flexible lightweight wing test piece; the displacement measuring device is arranged directly below the flexible lightweight wing test piece for measuring the displacement at different positions of the flexible lightweight wing test piece. The data monitoring and acquisition device is connected to the wing stiffness adjuster and the displacement measuring device, and is used to monitor and record the tension of the pull rope and the displacement at different positions of the flexible lightweight wing test piece in real time, so as to calculate the stiffness of the flexible lightweight wing test piece.

2. The variable stiffness lightweight airfoil static strength testing device as described in claim 1, characterized in that, The wing clamping fixture includes a wing clamping mold, a mold holder, and a holder fixing knob; Two opposing mold holders clamp the wing clamping mold in the middle and fix it to the mold assembly platform by the clamping holder fixing knob; The wing clamping mold is provided with a molded through hole that matches the airfoil shape at the wing root of the flexible lightweight wing test piece; the molded through hole extends along the spanwise direction of the flexible lightweight wing test piece and is used to clamp the wing root of the flexible lightweight wing test piece. The top surface of the wing clamping mold is provided with a through groove for accommodating the air nozzle of the flexible lightweight wing test piece; the air nozzle is used to connect to the inflation device.

3. The variable stiffness lightweight airfoil static strength testing device as described in claim 2, characterized in that, The mold holder is a rectangular structure made of high-strength alloy steel and has a groove on the side facing the wing where the mold is held. The wing clamping mold is provided with fixing latches on both sides facing the mold holder; The fixed tenon is fitted into the groove in a matching shape, and the longitudinal position of the wing clamping mold is adjusted by sliding the fixed tenon along the groove.

4. The variable stiffness lightweight airfoil static strength testing device as described in claim 3, characterized in that, The molding platform includes a wing clamping fixture base; The wing clamping fixture base is a thick-walled alloy steel structure, which is fixed to the ground by high-strength bolts. The top surface is provided with a clamping device sliding groove and a displacement scale. The bottom of the mold holder is provided with sliding latches that correspond one-to-one with the sliding grooves of the holder; The sliding tenon is slidably installed in the corresponding clamp sliding groove; The mold holder achieves lateral position adjustment of the wing clamping mold by sliding the sliding tenon along the sliding groove of the holder; The displacement scale is used to laterally position the mold holder when the sliding latch slides along the sliding groove of the holder, so as to accurately position the wing clamping mold held by the mold holder.

5. The variable stiffness lightweight airfoil static strength testing device as described in claim 2, characterized in that, The pull rope height adjustment device includes a gantry support platform, a main crossbeam, and a main crossbeam fixing knob; The bottom end of the portal beam support platform is located on both sides of the molding platform and fixed to the ground; The two ends of the main crossbeam are slidably engaged with the portal beam support platform, and can only slide vertically along the portal beam support platform; a tie post is formed in the middle of the main crossbeam, and the tie post is used to tie one end of the pull rope. The main crossbeam fixing knobs are installed at both ends of the main crossbeam to lock the main crossbeam to the door beam support platform, so that there is no slippage between the main crossbeam and the door beam support platform.

6. The variable stiffness lightweight airfoil static strength testing device as described in claim 5, characterized in that, The portal beam support platform includes a main support vertical beam, a main beam support triangular frame, a ground stabilizing frame, and a main horizontal beam sliding guide rail. The main support vertical beams are provided on both sides of the molding platform; the main support vertical beams are vertically placed square thick-walled beam structures and are fixed to the ground by tooling bolts; The main beam support triangle is vertically installed and welded to the main support vertical beam to enhance the longitudinal stability of the main support vertical beam. The ground stabilizing frame is horizontally set on the ground and welded to the bottom surface of the main beam support triangle to enhance the lateral stability of the main support vertical beam. The main crossbeam sliding guide rail is vertically arranged and fixedly installed on the inner side of the main support vertical beam facing the molding platform; The main crossbeam is slidably engaged with the main crossbeam sliding guide rail through the slots at both ends, so that it can only slide along the main crossbeam sliding guide rail in the vertical direction.

7. The variable stiffness lightweight airfoil static strength testing device as described in claim 6, characterized in that, The main crossbeam sliding guide rail is an I-beam shaped structure; the main support vertical beam has weight-reducing holes evenly distributed along the vertical direction.

8. The variable stiffness lightweight airfoil static strength testing device as described in claim 5, characterized in that, The wing stiffness adjuster includes two tie lugs, a sleeve bearing, an internally threaded screw-in sleeve, an externally threaded screw-in column, and a pull rope force gauge. The tethering lug includes a cylinder and a tethering ring; the tethering ring is used to connect and fasten the pull rope; one end of the cylinder is fixedly connected to the tethering ring, and the other end is equipped with a sleeve bearing; A pull rope is connected between the tethering ring of one of the tethering ears and the tethering post, and another pull rope is connected between the tethering ring of the other tethering ear and the flexible lightweight wing test piece. One sleeve bearing is externally connected to the internally threaded sleeve, and the other sleeve bearing is externally connected to the pull rope force gauge. The sleeve bearings enable both the internally threaded sleeve and the pull rope force gauge to rotate freely around the end lug. One end of the external thread screw-in column is fixedly connected to the pull rope force gauge, and the other end is threadedly connected to the internal thread screw-in sleeve. The preload of the pull rope is adjusted by the helical engagement of the external thread screw-in column and the internal thread screw-in sleeve. The pull rope force gauge is used to measure the tension of the pull rope and transmit the data to the data monitoring and acquisition device in real time.

9. The variable stiffness lightweight airfoil static strength testing device as described in any one of claims 2-8, characterized in that, The inflation device includes an air storage device, a pressure stabilizing device, a pressure display, and an inflation pipeline connected in sequence. The gas storage device is inflated and stores high-pressure gas using an air compressor; the gas storage device is connected to the pressure stabilizing device via an inflation valve; the pressure stabilizing device is used to achieve constant pressure output of the high-pressure gas; the pressure display is used to display the gas pressure; the inflation pipeline inputs the constant-pressure high-pressure gas into the flexible lightweight wing test piece through the air nozzle.

10. The static strength testing device for a variable stiffness lightweight airfoil as described in claim 8, characterized in that, The data monitoring and acquisition device includes a data monitoring display screen and a data processor; The data processor is connected to the displacement measuring device, the pull rope force gauge and the data monitoring display signal, and is used to monitor and record the tension of the pull rope and the displacement values ​​at different positions of the flexible lightweight wing test piece in real time. The loading counterweight is a flat sandbag; The displacement measuring device is a laser displacement sensor.

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