A testing device for the blade strength of a heavy-loaded UAV

Abstract

The present invention relates to the technical field of unmanned aerial vehicle manufacturing, and specifically to a testing device for the strength of heavy-loaded unmanned aerial vehicle blades, comprising a base, a support column fixedly mounted on the upper end face of the base, an equipment table fixedly mounted on the rear end face of the support column, and a fixing mechanism for clamping and fixing one end of the blade is provided on the support column. An integrated operation model of clamping, mobile testing, and variable counterweight is adopted to perform bending strength tests at different frequencies and different loads on different positions of the heavy-loaded unmanned aerial vehicle blades, thereby simulating various complex situations that the blades may encounter in actual flight, making the test results closer to actual applications, and comprehensively evaluating the strength, stiffness, and durability of the blades. At the same time, the test error caused by blade displacement or deflection is reduced through double fixation, thereby enhancing the test stability and improving the accuracy of the test results.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicle manufacturing, and in particular to a device for testing the strength of heavy-loaded unmanned aerial vehicle blades. Background Art

[0002] A heavy-load UAV refers to an unmanned aerial vehicle used to carry heavier payloads. It has broad application prospects in commercial logistics, agriculture, engineering construction and other fields. Blades are the most important component of a heavy-load UAV. Since heavy-load UAVs need to carry a large weight, their blades must not only be able to bear their own weight, but also be able to withstand aerodynamic loads under high-speed rotation. Therefore, the blades need to be strength tested, the most important of which is the bending strength test, which is used to test the bending strength of the blades under different loads to ensure that the blades can withstand these loads without structural damage, thereby ensuring that the heavy-load UAV is always in good working condition.

[0003] At present, there are the following shortcomings when testing the strength of heavy-loaded UAV blades: when performing a bending strength test, it is usually necessary to clamp and fix one end of the blade first, and then fix the swinging device on the upper end surface of the blade at a specific position, and then fix a load of a certain weight on the suspended part of the other end of the blade, start the swinging device to drive the blade to swing up and down, so as to test the bending strength of the blade. In the above process, only a single position of the blade is tested for bending strength, and each part of the blade has different stress distribution and structural characteristics, and the blade will experience complex load conditions in actual use. Therefore, the test results of a single position cannot represent the performance of the entire blade, and it is impossible to detect fatigue damage caused by repeated loads on the heavy-loaded UAV blades, and thus it is impossible to ensure that the blades will not suffer structural damage when subjected to these loads.

[0004] Therefore, in order to ensure that the heavy-loaded UAV is in good working condition after the blades are subjected to load, the present invention provides a testing device for the strength of heavy-loaded UAV blades. Summary of the invention

[0005] In order to solve the above technical problems, the present invention provides a testing device for the strength of heavy-loaded UAV blades, which is achieved by the following specific technical means: a testing device for the strength of heavy-loaded UAV blades, comprising a base, a support column is fixedly installed on the upper end face of the base, an equipment table is fixedly installed on the rear end face of the support column, and a fixing mechanism for clamping and fixing one end of the blade is arranged on the support column; the fixing mechanism comprises a clamping portion arranged on the support column, and the clamping portion is provided with a locking portion for auxiliary fixation thereof.

[0006] A testing mechanism that cooperates with the fixing mechanism and is used to perform a bending strength test on the blade is arranged above the base; the testing mechanism includes a moving part that is arranged above the base and is used to move and adjust the test position on the blade, the moving part is provided with a positioning part for fixing it at the blade test position and a limiting part for limiting its moving position, the moving part is also provided with a swinging part for swinging the blade at different frequencies, and a supporting part that cooperates with the moving part to provide support for the test process is arranged on the equipment table.

[0007] A load-bearing mechanism for applying different weights to the other end of the blade is arranged above the base, and the testing mechanism cooperates with the load-bearing mechanism to perform bending strength tests on the blade under different frequencies and different weights; the load-bearing mechanism includes a mounting portion arranged above the base and used to be fixed to the other end of the blade, and a weight-increasing portion is arranged on the mounting portion.

[0008] As a preferred technical solution of the present invention, the clamping part includes a support plate, a first screw sleeve, a first slideway, a clamping plate, a first screw and a first belt. A support plate corresponding to the equipment table is fixedly installed on the front end face of the support column, and the first screw sleeves are fixedly installed through the four corners of the support plate. A first slideway is provided on the front end face of the support column, and a clamping plate located directly above the support plate and corresponding to the support plate is slidably installed in the first slideway. The clamping plate is penetrated by left-right symmetrical sliding holes, and a first screw corresponding to the first screw sleeve is penetrated by a bearing on the clamping plate. The first screw sleeve is threadedly connected to the corresponding first screw, and the upper end of the first screw is connected through a first belt transmission.

[0009] As a preferred technical solution of the present invention, the locking part includes a second slide, a first slider, a positioning rod and a locking rod. The upper end surface of the clamping plate is provided with a left-right symmetrical second slide, and the first slider is slidably installed in the second slide. The upper end surface of the support plate is fixedly provided with a left-right symmetrical positioning rod that is slidably connected to the corresponding sliding hole. A locking hole is penetrated through the ring wall of the positioning rod, and a locking rod matching the corresponding locking hole is fixedly installed on a side wall of the first slider away from each other.

[0010] As a preferred technical solution of the present invention, the moving part includes a test plate, a first bracket, a shaped frame, a rubber roller and a first motor. A test plate for being placed on the upper end surface of the blade is arranged in front of the support plate, and a first bracket symmetrically mounted front and rear is fixedly mounted on the test plate. A shaped frame is hingedly connected to the side of the first bracket away from the test plate through a torsion spring rod, a matching shaft rod is installed in the shaped frame through a bearing, a rubber roller located in the shaped frame is fixedly sleeved on the matching shaft rod, and a first motor whose output end is fixedly connected to the corresponding matching shaft rod is fixedly mounted on the shaped frame on the rear side.

[0011] As a preferred technical solution of the present invention, the positioning part includes a second screw sleeve, a second belt, a second motor, a pressing plate and a second screw. The second screw sleeves are installed through bearings at the four corners of the test plate. The upper ends of the second screw sleeves are connected by a second belt. A second motor is fixedly installed on the test plate. The output end of the second motor is connected to one of the second screw sleeves through a first gear set. A corresponding pressing plate is arranged directly below the test plate. A second screw corresponding to the second screw sleeve is fixedly installed on the upper end surface of the pressing plate. The second screw is threadedly connected to the corresponding second screw sleeve.

[0012] As a preferred technical solution of the present invention, the limiting part includes a third slideway, a first bidirectional screw and a second slider. A third slideway is opened on the lower end surface of the test plate. The first bidirectional screw is installed through a bearing in the third slideway. Second sliders that are symmetric left and right and are threadedly connected to the first bidirectional screw are slidably installed in the third slideway. A limiting plate is arranged at the lower end of the second slider.

[0013] As a preferred technical solution of the present invention, the swinging part includes an equipment frame, a bearing seat, a central shaft, a third motor, a swing arm and a counterweight. An equipment frame is fixedly installed at the center of the upper end surface of the test plate. Symmetric left and right bearing seats are fixedly installed on the upper end surface of the equipment frame. A central shaft is jointly installed through bearings at the centers of the symmetric left and right bearing seats. A third motor is fixedly installed on the upper end surface of the equipment frame. The output end of the third motor is connected to the central shaft through a second gear set. Symmetric left and right swing arms are fixedly installed on the central shaft. A counterweight is fixedly installed at one end of the swing arm away from the central shaft.

[0014] As a preferred technical solution of the present invention, the supporting part includes a wire winder, an elastic rope, a guide wheel, a supporting seat and a hydraulic cylinder. A wire winder is fixedly installed on the upper end surface of the equipment table. The retracting end of the wire winder is fixedly installed with an elastic rope. Symmetric front and rear guide wheels are fixedly installed on the upper end surface of the supporting column. The other end of the elastic rope passes through the symmetric front and rear guide wheels and is fixedly connected to the upper end surface of the test plate. A supporting seat located between the symmetric front and rear guide wheels is fixedly installed on the upper end surface of the supporting column. A hydraulic cylinder with a telescopic end passing through the lower end surface of the supporting seat is fixedly installed on the supporting seat. A wire pressing plate is fixedly installed at the telescopic end of the hydraulic cylinder.

[0015] As a preferred technical solution of the present invention, the installation part includes a counterweight plate, a fourth slideway, a second bidirectional screw and a third slider. A counterweight plate for placing on the upper end surface of the front side of the blade is arranged in front of the test plate. A fourth slideway is opened on the lower end surface of the counterweight plate. The second bidirectional screw is installed through a bearing in the fourth slideway. Third sliders that are symmetric left and right and are threadedly connected to the second bidirectional screw are slidably installed in the fourth slideway. A U-shaped block is fixedly installed at the lower end of the third slider.

[0016] As a preferred technical solution of the present invention, the weight-increasing part includes a load-bearing block, an L-shaped buckle plate, an inclined groove and a matching groove. The upper end surface of the counterweight plate is hinged with a front-and-rear symmetrical L-shaped buckle plate through a torsion spring. The front-and-rear symmetrical L-shaped buckle plates are a group, and a number of groups of L-shaped buckle plates are evenly distributed in an array from right to left on the upper end surface of the counterweight plate. A load-bearing block located between the corresponding front-and-rear symmetrical L-shaped buckle plates is placed on the upper end surface of the counterweight plate. A front-and-rear symmetrical inclined groove is provided at the lower end of the load-bearing block, and a matching groove matching the L-shaped buckle plate is provided on the load-bearing block.

[0017] Compared with the prior art, the present invention has the following beneficial effects: 1. The heavy-load UAV blade strength testing device, through the coordinated use of the fixing mechanism, the testing mechanism and the load-bearing mechanism, adopts an integrated operation model of clamping fixation, mobile testing and variable counterweight, to perform bending strength tests at different frequencies and different loads on different positions of the heavy-load UAV blades, thereby simulating various complex situations that the blades may encounter in actual flight, making the test results closer to actual applications, and comprehensively evaluating the strength, stiffness and durability of the blades, and reducing the time for test preparation and adjustment, improving test efficiency, and at the same time reducing the test error caused by blade displacement or deflection through double fixation, enhancing the test stability, thereby ensuring the safety and reliability of the UAV under extreme conditions, so that the blades can still ensure that the heavy-load UAV is in good working condition after bearing the load.

[0018] 2. The heavy-load UAV blade strength test device, through the set fixing mechanism, after clamping and fixing one end of the heavy-load UAV blade, performs lateral locking to assist in fixing the blade, ensuring that the blade maintains the correct position and angle during the test, reducing the test error caused by blade displacement or deflection, and can increase the stability of the blade during the test, prevent the blade from unnecessary vibration or rotation when subjected to bending force, and at the same time simulate the lateral load that the blade is subjected to in actual work, so that the test result is closer to actual usage.

[0019] 3. The heavy-load UAV blade strength test device can automatically translate and fix on the heavy-load UAV blade through the set test mechanism, so as to perform bending strength tests of different frequencies on different positions of the blade, so as to better simulate the complex loads that the blade bears in the actual working environment, and help to comprehensively evaluate the strength and durability of the blade at different positions under different conditions. At the same time, the blade can be subjected to repeated load fatigue tests to detect fatigue damage of the blade. During the test, the triangle constructed by the elastic rope and the support column provides additional support points for the blade, which enhances the stability during the test and reduces the test error.

[0020] 4. The heavy-load UAV blade strength test device can conduct bending strength tests of heavy-load UAV blades at different frequencies under different loads through the coordinated use of the set testing mechanism and the load-bearing mechanism, so as to comprehensively evaluate the strength, stiffness and durability of the blades under different working conditions, and understand the bending strength of the blades under different conditions, which helps to ensure the safety and reliability of the UAV under extreme conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention when it is working.

[0022] Figure 2 It is a schematic diagram of a partial three-dimensional structure viewed from above of the present invention.

[0023] Figure 3 It is a three-dimensional structural schematic diagram of the fixing mechanism of the present invention.

[0024] Figure 4 It is a partial three-dimensional structural schematic diagram of the testing mechanism of the present invention.

[0025] Figure 5 It is a bottom-up stereoscopic structural schematic diagram of the limiting portion of the present invention.

[0026] Figure 6 It is a schematic diagram of the three-dimensional structure of the support part of the present invention.

[0027] Figure 7 It is a partially cutaway three-dimensional structural schematic diagram of the load-bearing mechanism of the present invention.

[0028] In the figure: 1, base; 2, support column; 3, equipment table; 4, fixing mechanism; 41, clamping part; 411, support plate; 412, first screw sleeve; 413, first slideway; 414, clamping plate; 415, first screw; 416, first belt; 42, locking part; 421, second slideway; 422, first slider; 423, positioning rod; 424, locking rod; 5, testing mechanism; 51, moving part; 511, testing board; 512, first bracket; 513, shaped frame; 514, rubber roller; 515, first motor; 52, positioning part; 521, second screw sleeve; 522, second belt; 523, second motor; 524, pressing plate; 525, second Screw rod; 53, limiting part; 531, third slideway; 532, first bidirectional screw rod; 533, second slider; 54, swinging part; 541, equipment frame; 542, bearing seat; 543, central axis; 544, third motor; 545, swing arm; 546, counterweight; 55, supporting part; 551, winding machine; 552, elastic rope; 553, guide wheel; 554, supporting seat; 555, hydraulic cylinder; 6, load-bearing mechanism; 61, mounting part; 611, counterweight plate; 612, fourth slideway; 613, second bidirectional screw rod; 614, third slider; 62, weight-increasing part; 621, load-bearing block; 622, L-shaped buckle plate; 623, inclined groove; 624, matching groove. DETAILED DESCRIPTION

[0029] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0030] See also Figure 1 A testing device for the strength of heavy-loaded UAV blades includes a base 1, a support column 2 is fixedly installed on the upper end surface of the base 1, an equipment platform 3 is fixedly installed on the rear end surface of the support column 2, and a fixing mechanism 4 for clamping and fixing one end of the blade is arranged on the support column 2; the fixing mechanism 4 includes a clamping portion 41 arranged on the support column 2, and a locking portion 42 for auxiliary fixing thereof is arranged on the clamping portion 41.

[0031] See also Figure 1A testing mechanism 5 is arranged above the base 1 and cooperates with the fixing mechanism 4 and is used to perform a bending strength test on the blade; the testing mechanism 5 includes a moving part 51 arranged above the base 1 and used to move and adjust the test position on the blade, the moving part 51 is provided with a positioning part 52 for fixing it at the blade test position and a limiting part 53 for limiting its moving position, the moving part 51 is also provided with a swinging part 54 for swinging the blade at different frequencies, and the equipment table 3 is provided with a supporting part 55 for cooperating with the moving part 51 to provide support for the test process.

[0032] See also Figure 1 A load-bearing mechanism 6 for applying different weights to the other end of the blade is arranged above the base 1. The testing mechanism 5 cooperates with the load-bearing mechanism 6 to perform bending strength tests on the blade under different frequencies and different weights. The load-bearing mechanism 6 includes a mounting portion 61 arranged above the base 1 and used to be fixed to the other end of the blade, and a weight-increasing portion 62 is arranged on the mounting portion 61.

[0033] See also Figure 1 , Figure 2 and Figure 3 The clamping portion 41 includes a support plate 411, a first screw sleeve 412, a first slideway 413, a clamping plate 414, a first screw rod 415 and a first belt 416. A support plate 411 corresponding to the equipment table 3 is fixedly installed on the front end surface of the support column 2, and the first screw sleeves 412 are fixedly installed through the four corners of the support plate 411. A first slideway 413 is provided on the front end surface of the support column 2. A clamping plate 414 located directly above the support plate 411 and corresponding to the support plate 411 is slidably installed in the first slideway 413. The clamping plate 414 is penetrated with left-right symmetrical sliding holes, and the clamping plate 414 is penetrated with a first screw rod 415 corresponding to the first screw sleeve 412 one by one through a bearing. The first screw sleeve 412 is threadedly connected to the corresponding first screw rod 415, and the upper end of the first screw rod 415 is connected by a transmission belt 416.

[0034] See also Figure 1 and Figure 3 The locking portion 42 includes a second slide 421, a first slider 422, a positioning rod 423 and a locking rod 424. The upper end surface of the clamping plate 414 is provided with a left-right symmetrical second slide 421, and the first slider 422 is slidably installed in the second slide 421. The upper end surface of the support plate 411 is fixedly provided with a left-right symmetrical positioning rod 423 that is slidably connected to the corresponding sliding hole. A locking hole is penetrated through the ring wall of the positioning rod 423, and a locking rod 424 that cooperates with the corresponding locking hole is fixedly installed on a side wall of the first slider 422 that is away from each other.

[0035] During specific work, when it is necessary to perform a bending strength test on the heavy-loaded UAV blade, first place the fixed end of the blade between the support plate 411 and the clamping plate 414, and fit the rear end of the blade with the front end of the support column 2, and then use an electric rotary tool to rotate one of the first screws 415, and the first screw 415 will rotate synchronously through the first belt 416, and when the first screw 415 contacts the first screw sleeve 412, the clamping plate 414 will move closer to the support plate 411 until the support plate 411 and the clamping plate 414 fix the fixed end of the blade, thereby completing the clamping and fixing of the blade, and a rubber plate is provided on the side where the support plate 411 and the clamping plate 414 are close to each other to protect the blade surface during the test.

[0036] During the movement of the clamping plate 414 toward the supporting plate 411, the positioning rod 423 passes through the sliding hole. When the blade is clamped, the locking hole on the positioning rod 423 and the locking rod 424 are in a coaxial position. Then the worker manually pushes the first sliders 422 on both sides toward the corresponding positioning rods 423 until the locking rods 424 are inserted into the locking holes. The outer ring wall of the positioning rod 423 is coated with a rubber layer to increase the friction between it and the locking hole to prevent the positioning rod 423 from detaching from the locking hole, thereby laterally locking the clamping plate 414 to assist in fixing the blade and ensure that the blade maintains the correct position and angle during the test.

[0037] See also Figure 1 , Figure 2 , Figure 4 , Figure 5 and Figure 6 The moving part 51 includes a test plate 511, a first bracket 512, a shaped frame 513, a rubber roller 514 and a first motor 515. A test plate 511 for placing on the upper end surface of the blade is arranged in front of the support plate 411, and a first bracket 512 symmetrically arranged in front and back is fixedly installed on the test plate 511. The side of the first bracket 512 away from the test plate 511 is hinged with a shaped frame 513 through a torsion spring rod. A matching shaft rod is installed in the shaped frame 513 through a bearing, and a rubber roller 514 located in the shaped frame 513 is fixedly sleeved on the matching shaft rod. A first motor 515 whose output end is fixedly connected to the corresponding matching shaft rod is fixedly installed on the shaped frame 513 located on the rear side.

[0038] See also Figure 1 , Figure 2 , Figure 4 , Figure 5 and Figure 6The positioning portion 52 includes a second screw sleeve 521, a second belt 522, a second motor 523, a pressure plate 524 and a second screw 525. The second screw sleeves 521 are installed through bearings at the four corners of the test plate 511. The upper end of the second screw sleeve 521 is connected by a second belt 522. The second motor 523 is fixedly installed on the test plate 511. The output end of the second motor 523 is connected to one of the second screw sleeves 521 by a first gear set. A pressure plate 524 corresponding to the test plate 511 is arranged directly below the test plate 511. The upper end surface of the pressure plate 524 is fixedly installed with a second screw 525 corresponding to the second screw sleeve 521. The second screw 525 is threadedly connected to the corresponding second screw sleeve 521.

[0039] See also Figure 1 , Figure 2 and Figure 5 The limiting part 53 includes a third slide 531, a first bidirectional screw 532 and a second slider 533. The lower end surface of the test plate 511 is provided with a third slide 531, and the first bidirectional screw 532 is installed through the third slide 531 through a bearing. The second slider 533 threadedly connected with the first bidirectional screw 532 and symmetrical to the left and right is slidably installed in the third slide 531, and a limiting plate is arranged at the lower end of the second slider 533.

[0040] During specific operation, after the fixing mechanism 4 completes the fixing of the blade, the test plate 511 is placed on the upper end surface of the blade. At this time, the molded frame 513, under the action of the torsion spring rod, brings the rubber rollers 514 on the front and rear sides into contact with the upper end surface of the blade, and then the first bidirectional screw 532 is rotated by an electric rotating tool, thereby driving the second sliders 533 on both sides to approach the blade synchronously, and the first bidirectional screw 532 is stopped when the second sliders 533 on both sides bring the corresponding limit plates to contact the blade. When the rubber roller 514 drives the test plate 511 to move on the upper end surface of the blade, the limit plates on both sides will limit the moving direction of the test plate 511, thereby ensuring that the test plate 511 always moves along the upper end surface of the blade.

[0041] Then, the first motor 515 is started to drive the rubber roller 514 to rotate, so that the rubber roller 514 drives the test plate 511 to move on the upper end surface of the blade, and when the test plate 511 moves to the corresponding position of the blade, the first motor 515 is stopped, and then the pressure plate 524 is placed directly below the test plate 511. At this time, the blade is located between the pressure plate 524 and the test plate 511, and then the second motor 523 is started to rotate the second screw sleeve 521 through the first gear set, and the second screw sleeve 521 rotates synchronously with the cooperation of the second belt 522. When the second screw sleeve 521 contacts the second screw rod 525 on the pressure plate 524, it will drive the pressure plate 524 to move upward until the pressure plate 524 squeezes the lower end surface of the blade. At this time, the test plate 511 squeezes the rubber roller 514 downward, so that the test plate 511 is fixed on the blade. A rubber plate is also provided on the side where the test plate 511 and the pressure plate 524 are close to each other to protect the surface of the blade during the test.

[0042] When the swing part 54 completes the test on the blade position, the second motor 523 is started in reverse so that the pressure plate 524 moves away from the blade and the second screw 525 does not separate from the second screw sleeve 521, thereby releasing the fixation of the test plate 511, and then the first motor 515 is started to drive the test plate 511 to move on the blade, and the fixing operation is repeated after reaching the corresponding position, so that the bending strength test can be performed on different positions of the blade.

[0043] See also Figure 1 , Figure 2 , Figure 4 and Figure 5 The swinging part 54 includes an equipment frame 541, a bearing seat 542, a central axis 543, a third motor 544, a swing arm 545 and a counterweight 546. The equipment frame 541 is fixedly installed at the center of the upper end surface of the test plate 511, and a left-right symmetrical bearing seat 542 is fixedly installed on the upper end surface of the equipment frame 541. The central axis 543 is jointly installed at the center of the left-right symmetrical bearing seat 542 through a bearing. The third motor 544 is fixedly installed on the upper end surface of the equipment frame 541, and the output end of the third motor 544 is connected to the central axis 543 through a second gear set. A left-right symmetrical swing arm 545 is fixedly installed on the central axis 543, and a counterweight 546 is fixedly installed on the end of the swing arm 545 away from the central axis 543.

[0044] See also Figure 1 , Figure 2 , Figure 4 and Figure 6The support part 55 includes a wire winder 551, an elastic rope 552, a guide wheel 553, a support seat 554 and a hydraulic cylinder 555. The wire winder 551 is fixedly installed on the upper end surface of the equipment table 3, and the elastic rope 552 is fixedly installed on the retracted end of the wire winder 551. The upper end surface of the support column 2 is fixedly installed with a front-to-back symmetrical guide wheel 553. The other end of the elastic rope 552 passes through the front-to-back symmetrical guide wheel 553 and is fixedly connected to the upper end surface of the test plate 511. The upper end surface of the support column 2 is fixedly installed with a support seat 554 located between the front-to-back symmetrical guide wheels 553. A hydraulic cylinder 555 is fixedly installed on the support seat 554, and the telescopic end of the hydraulic cylinder 555 passes through the lower end surface of the support seat 554. A wire pressing plate is fixedly installed on the telescopic end of the hydraulic cylinder 555.

[0045] During specific operation, after the test plate 511 is fixed at the corresponding position of the blade, the hydraulic pump (not shown in the figure) fixedly installed on the support column 2 is started, so that the hydraulic cylinder 555 carries the wire pressing plate to press the elastic rope 552 below it onto the support column 2. When the blade swings up and down under the action of the swing part 54, the elastic rope 552 located in front of the wire pressing plate will expand and contract accordingly. At this time, the triangle constructed by the elastic rope 552, the blade and the support column 2 provides an additional support point for the blade, enhances the stability during the test, and reduces the test error. When it is necessary to test other positions of the blade, the hydraulic cylinder 555 is started in the reverse direction to release the fixation of the elastic rope 552, so that the test plate 511 can pull the elastic rope 552.

[0046] After the test plate 511 is fixed at the corresponding position of the blade, the third motor 544 is started to rotate the central axis 543 through the second gear set, and the central axis 543 will rotate with the swing arm 545 around the central axis 543 as the center point. At this time, the test plate 511 with the swing part 54 corresponds to the suspended position of the blade. In the process of the swing arm 545 rotating with the counterweight 546, centrifugal force will be generated, and the suspended part of the blade will be driven up and down by the centrifugal force, so as to test the bending strength of the blade at this position, and by adjusting the rotation speed of the third motor 544, the bending strength test of the blade at this position is performed at different frequencies. During this test, if the blade breaks or bends in an irreversible manner, it means that the bending strength of the blade is unqualified, otherwise the bending strength is qualified, so as to better simulate the complex loads that the blade bears in the actual working environment, which is helpful to comprehensively evaluate the strength and durability of the blade at different positions under different conditions. At the same time, the blade can be subjected to repeated load fatigue test to detect fatigue damage of the blade.

[0047] See also Figure 1 , Figure 2 and Figure 7, the installation part 61 includes a counterweight plate 611, a fourth slideway 612, a second bidirectional screw 613 and a third slider 614. In front of the test plate 511, there is a counterweight plate 611 for placing on the upper front end face of the blade. The lower end face of the counterweight plate 611 is provided with a fourth slideway 612. A second bidirectional screw 613 is installed through the fourth slideway 612 by means of bearings. In the fourth slideway 612, there are two symmetrically arranged third sliders 614 that are threadedly connected to the second bidirectional screw 613. The lower ends of the third sliders 614 are fixedly installed with U-shaped blocks.

[0048] Please refer to Figure 1 and Figure 7 , the weight-increasing part 62 includes a load block 621, an L-shaped buckle plate 622, an inclined surface groove 623 and a mating groove 624. The upper end face of the counterweight plate 611 is hinged with symmetrically arranged front and rear L-shaped buckle plates 622 through torsion springs. The L-shaped buckle plates 622 are made of a metal material with a certain elasticity. The symmetrically arranged front and rear L-shaped buckle plates 622 form a group, and several groups of L-shaped buckle plates 622 are evenly distributed in an array from right to left on the upper end face of the counterweight plate 611. A load block 621 located between the corresponding symmetrically arranged front and rear L-shaped buckle plates 622 is placed on the upper end face of the counterweight plate 611. The lower end of the load block 621 is provided with symmetrically arranged front and rear inclined surface grooves 623. The load block 621 is provided with a mating groove 624 that mates with the L-shaped buckle plate 622.

[0049] During specific operation, when it is necessary to conduct a load-bearing bending strength test on the blade, place the counterweight plate 611 on the upper front end face of the blade, and use an electric rotary tool to rotate the second bidirectional screw 613, thereby driving the two third sliders 614 to approach the front side of the blade until the two third sliders 614 drive the corresponding U-shaped blocks to clamp the front end of the blade, so as to fix the counterweight plate 611 at the front end of the blade.

[0050] Subsequently, place the load block 621 on the counterweight plate 611. During the placement process, the load block 621 will push the two L-shaped buckle plates 622 to both sides through the inclined surface grooves 623. When the horizontal section of the L-shaped buckle plate 622 corresponds to the position of the mating groove 624, the horizontal section of the L-shaped buckle plate 622 will be buckled into the mating groove 624 under the action of the torsion spring, so as to fix the load block 621 on the counterweight plate 611. Subsequently, by continuously adjusting the number of load blocks 621, the weight at the front end of the blade is increased, and in cooperation with the swinging part 54, a bending strength test of different frequencies under different loads is carried out on the blade. At the same time, in cooperation with the moving part 51, a bending strength test combining different loads and different frequencies can be carried out at different positions of the blade. During this test process, if the blade breaks or has a non-recoverable bend, it means that the bending strength of the blade is unqualified. On the contrary, the bending strength is qualified, so as to comprehensively evaluate the strength, stiffness and durability of the blade under different working conditions, and the bending strength of the blade under different conditions can be understood.

[0051] Please refer to Figure 1 — Figure 7 Working principle: When it is necessary to perform a bending strength test on the heavy-loaded UAV blade, first place the fixed end of the blade between the support plate 411 and the clamping plate 414, and fit the rear end of the blade with the front end of the support column 2, then use an electric rotary tool to rotate one of the first screws 415, and complete the clamping and fixing of the blade through the clamping part 41, and then use the locking part 42 to laterally lock the clamping plate 414 to assist in fixing the blade.

[0052] Next, place the test plate 511 on the upper end surface of the blade, limit the moving direction of the test plate 511 by the limit portion 53, then start the first motor 515 to drive the test plate 511 to move to the corresponding position of the blade through the moving portion 51, then place the pressure plate 524 directly under the test plate 511, and fix the test plate 511 on the blade through the cooperation of the moving portion 51 and the positioning portion 52.

[0053] Then start the hydraulic pump fixed on the support column 2 to provide an additional support point for the blade through the support part 55 to enhance the stability during the test. Then start the third motor 544 to test the bending strength of the blade at this position through the swing part 54, and by adjusting the rotation speed of the central axis 543 driven by the third motor 544, the bending strength test of different frequencies can be performed on the blade at this position. During this test, if the blade is broken or bent in an irreversible manner, it means that the bending strength of the blade is unqualified, otherwise the bending strength is qualified.

[0054] When it is necessary to perform a load bending strength test on the blade, the weight of the front end of the blade is increased by the load-bearing mechanism 6, and the bending strength test of the blade at different frequencies under different loads is performed in cooperation with the swinging part 54. At the same time, the bending strength test combining different loads and different frequencies is performed at different positions of the blade in cooperation with the moving part 51. During this test process, if the blade breaks or bends in an irreversible manner, it means that the bending strength of the blade is unqualified. Otherwise, the bending strength is qualified. In this way, the bending strength test of the heavy-loaded UAV blade is completed.

[0055] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A heavy-load UAV blade strength testing device, comprising a base (1), characterized in that: A support column (2) is fixedly mounted on the upper end surface of the base (1), an equipment platform (3) is fixedly mounted on the rear end surface of the support column (2), and a fixing mechanism (4) for clamping and fixing one end of the blade is provided on the support column (2); The fixing mechanism (4) comprises a clamping portion (41) arranged on the support column (2), and a locking portion (42) for auxiliary fixing thereof is arranged on the clamping portion (41); A testing mechanism (5) is arranged above the base (1) and cooperates with the fixing mechanism (4) and is used to perform a bending strength test on the blade; The testing mechanism (5) comprises a moving part (51) arranged above the base (1) and used to move and adjust the testing position on the blade; the moving part (51) is provided with a positioning part (52) used to fix it at the blade testing position and a limiting part (53) used to limit its moving position; the moving part (51) is also provided with a swinging part (54) used to swing the blade at different frequencies; and the equipment stand (3) is provided with a supporting part (55) used to cooperate with the moving part (51) to provide support for the testing process; A load-bearing mechanism (6) is arranged above the base (1) for applying different weights to the other end of the blade, and the testing mechanism (5) cooperates with the load-bearing mechanism (6) to perform a bending strength test on the blade under different frequencies and different weights; The load-bearing mechanism (6) comprises a mounting portion (61) arranged above the base (1) and used for fixing to the other end of the blade, and a weight-increasing portion (62) is arranged on the mounting portion (61).

2. The heavy-load UAV blade strength testing device according to claim 1 is characterized by: The clamping part (41) comprises a support plate (411), a first screw sleeve (412), a first slideway (413), a clamping plate (414), a first screw rod (415) and a first belt (416); a support plate (411) corresponding to the equipment platform (3) is fixedly installed on the front end surface of the support column (2); the first screw sleeve (412) is fixedly installed through the four corners of the support plate (411); a first slideway (413) is opened on the front end surface of the support column (2); the first slideway (413) ) is slidably installed in the support plate (411), and a clamping plate (414) is located directly above the support plate (411) and corresponds to the support plate (411). The clamping plate (414) is provided with sliding holes that are symmetrical on both sides. A first screw rod (415) corresponding to the first screw sleeve (412) is installed on the clamping plate (414) through a bearing. The first screw sleeve (412) is threadedly connected to the corresponding first screw rod (415), and the upper end of the first screw rod (415) is connected through a first belt (416) for transmission.

3. The heavy-load UAV blade strength testing device according to claim 2 is characterized by: The locking portion (42) comprises a second slideway (421), a first slider (422), a positioning rod (423) and a locking rod (424); the upper end surface of the clamping plate (414) is provided with a left-right symmetrical second slideway (421); the first slider (422) is slidably installed in the second slideway (421); the upper end surface of the support plate (411) is fixedly provided with a left-right symmetrical positioning rod (423) slidably connected to the corresponding sliding hole; a locking hole is penetrated through the ring wall of the positioning rod (423); and a locking rod (424) matching the corresponding locking hole is fixedly installed on a side wall of the first slider (422) away from each other.

4. The heavy-load UAV blade strength testing device according to claim 2 is characterized by: The moving part (51) comprises a test plate (511), a first bracket (512), a shaped frame (513), a rubber roller (514) and a first motor (515); a test plate (511) for being placed on the upper end surface of a blade is arranged in front of the support plate (411); a first bracket (512) symmetrically arranged in front and rear is fixedly mounted on the test plate (511); a shaped frame (513) is hingedly connected to a side of the first bracket (512) away from the test plate (511) through a torsion spring rod; a matching shaft rod is installed in the shaped frame (513) through a bearing; a rubber roller (514) located in the shaped frame (513) is fixedly sleeved on the matching shaft rod; and a first motor (515) whose output end is fixedly connected to the corresponding matching shaft rod is fixedly mounted on the shaped frame (513) located at the rear side.

5. The heavy-load UAV blade strength testing device according to claim 4 is characterized by: The positioning part (52) comprises a second screw sleeve (521), a second belt (522), a second motor (523), a pressure plate (524) and a second screw rod (525). The second screw sleeves (521) are installed through bearings at the four corners of the test plate (511). The upper end of the second screw sleeve (521) is connected by transmission via a second belt (522). The second motor (523) is fixedly installed on the test plate (511). The output end of the second motor (523) is connected by transmission to one of the second screw sleeves (521) via a first gear set. A pressure plate (524) corresponding to the test plate (511) is arranged directly below the test plate (511). A second screw rod (525) corresponding to the second screw sleeve (521) is fixedly installed on the upper end surface of the pressure plate (524). The second screw rod (525) is threadedly connected to the corresponding second screw sleeve (521).

6. The heavy-load UAV blade strength testing device according to claim 4 is characterized by: The limiting portion (53) comprises a third slideway (531), a first bidirectional screw rod (532) and a second slider (533); the third slideway (531) is provided on the lower end surface of the test plate (511); the first bidirectional screw rod (532) is installed in the third slideway (531) through a bearing; a second slider (533) is slidably installed in the third slideway (531) and is threadedly connected to the first bidirectional screw rod (532) and is symmetrical to the left and right; a limiting plate is provided at the lower end of the second slider (533).

7. The heavy-load UAV blade strength testing device according to claim 4 is characterized by: The swing part (54) includes an equipment frame (541), a bearing seat (542), a central shaft (543), a third motor (544), a swing arm (545) and a counterweight (546). An equipment frame (541) is fixedly installed at the center of the upper end surface of the test plate (511). Symmetrically left and right bearing seats (542) are fixedly installed on the upper end surface of the equipment frame (541). A central shaft (543) is jointly installed through bearings at the centers of the symmetrically left and right bearing seats (542). A third motor (544) is fixedly installed on the upper end surface of the equipment frame (541). The output end of the third motor (544) is传动连接与中心轴(543)通过设置的第二齿轮组传动连接,中心轴(543)上固定安装有左右对称的摆臂(545),摆臂(545)远离中心轴(543)的一端固定安装有配重块(546)。 8. The heavy-load UAV blade strength testing device according to claim 4 is characterized by: The support part (55) includes a wire winding machine (551), an elastic rope (552), a guide wheel (553), a support seat (554) and a hydraulic cylinder (555). A wire winding machine (551) is fixedly installed on the upper end surface of the equipment table (3). The retracting end of the wire winding machine (551) is fixedly installed with an elastic rope (552). Symmetrically front and rear guide wheels (553) are fixedly installed on the upper end surface of the support column (2). The other end of the elastic rope (552) passes through the symmetrically front and rear guide wheels (553) and is fixedly connected to the upper end surface of the test plate (511). A support seat (554) is fixedly installed on the upper end surface of the support column (2) between the symmetrically front and rear guide wheels (553). A hydraulic cylinder (555) with a telescopic end penetrating the lower end surface of the support seat (554) is fixedly installed on the support seat (554). The telescopic end of the hydraulic cylinder (555) is fixedly installed with a wire pressing plate.

9. The heavy-load UAV blade strength testing device according to claim 4, characterized in that: The installation part (61) includes a counterweight plate (611), a fourth slideway (612), a second bidirectional screw (613) and a third slider (614). In front of the test plate (511), there is a counterweight plate (611) for placing on the upper end surface of the front side of the blade. A fourth slideway (612) is opened on the lower end surface of the counterweight plate (611). A second bidirectional screw (613) is installed through the fourth slideway (612) through bearings. In the fourth slideway (612), symmetrically left and right third sliders (614) that are threadedly connected to the second bidirectional screw (613) are slidably installed. A U-shaped block is fixedly installed at the lower end of the third slider (614). It should be noted that there is an unclear expression "传动连接与中心轴(543)通过设置的第二齿轮组传动连接" in the translation of , which needs to be further clarified in the original text for a more accurate translation.

10. The heavy-load UAV blade strength testing device according to claim 9, characterized in that: The weight-increasing part (62) comprises a load-bearing block (621), an L-shaped buckle plate (622), an inclined groove (623) and a matching groove (624); the upper end surface of the counterweight plate (611) is hinged with a front-to-back symmetrical L-shaped buckle plate (622) through a torsion spring; the front-to-back symmetrical L-shaped buckle plates (622) form a group, and a plurality of groups of L-shaped buckle plates (622) are evenly distributed in an array manner from right to left on the upper end surface of the counterweight plate (611); a load-bearing block (621) located between the corresponding front-to-back symmetrical L-shaped buckle plates (622) is placed on the upper end surface of the counterweight plate (611); a front-to-back symmetrical inclined groove (623) is provided at the lower end of the load-bearing block (621); and a matching groove (624) matching with the L-shaped buckle plate (622) is provided on the load-bearing block (621).

Images