Wing performance testing device
By introducing components such as vibration motors, slide rails, and electric cylinders into the wing performance testing device, the multi-degree-of-freedom motion and angle changes of the wing are simulated, solving the problem of deviation between test results and actual flight performance in existing technologies, and achieving higher-precision performance testing.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-01-28
- Publication Date
- 2026-03-17
AI Technical Summary
Existing wing performance testing devices cannot simulate the changes in mechanical and electrical properties under multi-degree-of-freedom motion states during actual flight of UAVs, resulting in a large deviation between test results and actual flight performance.
A wing performance testing device was designed. By setting up components such as vibration motors, slide rails, sliders, slide tables, and electric cylinders on the upper and lower support frames, the device simulates the multi-degree-of-freedom motion and angle changes of the wing. Combined with the controller to control the start and stop of the motors and electric cylinders, the device can accurately simulate the wing under different angles and vibrations.
It improves the experimental precision of wing performance testing, enabling more realistic simulation of the mechanical and electrical performance changes of the wing under complex flight conditions, and the test results are closer to actual performance.
Smart Images
Figure CN121671902A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of unmanned aerial vehicle (UAV) research and development, and in particular to a wing performance testing device. Background Technology
[0002] The rapid development of UAV technology has placed higher demands on wing performance, especially on stability and reliability under complex flight conditions. Currently, UAV wing performance testing mainly relies on two types of devices: one type uses bolts to fix the wing to a rigid support, which can only perform static mechanical loading tests; the other type uses a vibration test bench to conduct vibration tests on the wing, which can simulate more complex vibration conditions. However, modern wings need to consider both aerodynamic and mechanical performance. They typically incorporate conformal antennas and other electronic components, and changes in mechanical performance affect the electrical performance of these antennas. The two methods mentioned above cannot simulate the changes in mechanical and electrical performance under the multi-degree-of-freedom motion conditions of actual UAV flight, leading to significant deviations between test results and actual flight performance. Summary of the Invention
[0003] The purpose of this application is to provide a wing performance testing device to solve the problems mentioned in the background art.
[0004] The wing performance testing device provided in this application adopts the following technical solution: A wing performance testing device includes an upper support frame and a lower support frame. A mounting plate is fixedly mounted on the upper end of the upper support frame. A first vibration motor is fixedly mounted on the lower end of the mounting plate, and a second vibration motor is fixedly mounted near the first vibration motor on the lower end of the mounting plate. The first and second vibration motors are distributed at a perpendicular angle. First slide rails are fixedly mounted on both sides of the upper end of the mounting plate. Two first sliders are slidably mounted on the outer sides of the two first slide rails. Mounting blocks are fixedly mounted on the upper ends of the two first sliders. A movable plate is fixedly mounted between the two mounting blocks. Second slide rails are fixedly mounted on both sides of the upper end of the movable plate. Second sliders are slidably mounted on the outer sides of the two second slide rails. Fixed plates are fixedly mounted on the upper ends of the four second sliders. Connecting seats are rotatably mounted on the upper ends of the four fixed plates. Carrier plates are fixedly mounted on two corresponding connecting seats among the four connecting seats. A hinge is provided between the two carrier plates. Mounting boxes are fixedly mounted on the upper ends of the two carrier plates. By adopting the above technical solution, the wings are installed inside two mounting boxes during use. Then, the second electric cylinder is activated. The extension and retraction of the second electric cylinder will cause the carrier plate with the rotating seat to move and change its angle. Since the two carrier plates are connected by a hinge, the angle of the other carrier plate will change simultaneously, thereby changing the angle between the two wings and simulating different wing installation angles. Afterwards, the first vibration motor and the second vibration motor are activated by the controller. The first vibration motor and the second vibration motor are distributed at a perpendicular angle to each other, which can simulate vibration at different angles, thereby more realistically simulating the actual flight state of the wing and improving the experimental accuracy.
[0005] Preferably, a first bidirectional lead screw is rotatably installed inside each of the two mounting boxes. A first slide is threaded onto the outer ends of both ends of the first bidirectional lead screw. A first mounting seat is fixedly installed on the upper end of each of the two first slides. A first guide rod is fixedly installed on both sides of the first bidirectional lead screw inside the mounting box. The two first guide rods are slidably connected to the first slides. A first motor is fixedly installed at one end of the mounting box. The output end of the first motor is fixedly connected to one end of the first bidirectional lead screw. By adopting the above technical solution, when in use, the first motor is started, and the first motor drives the first bidirectional lead screw to rotate. The rotation of the first bidirectional lead screw will drive the two first slides and the first mounting base to move in opposite directions, thereby changing the distance between the two first mounting bases.
[0006] Preferably, a second bidirectional lead screw is rotatably arranged inside the mounting box, and a second slide is threaded onto both ends of the second bidirectional lead screw. A second mounting seat is fixedly arranged on the upper end of each of the two second slides. A second guide rod is fixedly arranged on both sides of the second bidirectional lead screw inside the mounting box. The two second guide rods are slidably connected to the two second slides. A second motor is fixedly arranged on one side of the mounting box, and the output end of the second motor is fixedly connected to one end of the second bidirectional lead screw. By adopting the above technical solution, when the second motor is started during use, the second motor will drive the second bidirectional lead screw to rotate, thereby causing the two second slides and the second mounting base to move in opposite directions, thus changing the distance between the two second mounting bases.
[0007] Preferably, a first electric cylinder mounting bracket is fixedly provided on one side of the lower end of the mounting plate, a first electric cylinder is fixedly provided on the lower end of the first electric cylinder mounting bracket, a connecting plate is fixedly provided on one side of the movable plate, and the telescopic end of the first electric cylinder is fixedly connected to the surface of the connecting plate. By adopting the above technical solution, when the first electric cylinder is activated during use, the extension and retraction of the first electric cylinder will drive the connecting plate to move, thereby causing the moving plate to swing.
[0008] Preferably, a second electric cylinder mounting bracket is fixedly provided at the lower end of the mounting plate, and a second electric cylinder is fixedly provided at the lower end of the second electric cylinder mounting bracket. A rotating seat is fixedly provided at the lower end of the two carrier plates corresponding to the position of the second electric cylinder. Both the mounting plate and the movable plate have through holes. The telescopic end of the second electric cylinder passes through the two through holes and is rotatably connected to the rotating seat. By adopting the above technical solution, after the second electric cylinder is started, the second electric cylinder will drive the carrier plate to move. Since the two carrier plates are connected by a hinge, the angle between the two carrier plates will change during the movement.
[0009] Preferably, the lower end of the upper support frame is fixedly provided with four first spring mounting seats arranged in a matrix array, the lower end of the lower support frame is fixedly provided with four legs arranged in a matrix array, and the upper end of the lower support frame is fixedly provided with four second spring mounting seats arranged in a matrix array. The four second spring mounting seats correspond to the positions of the four first spring mounting seats respectively, and the first spring mounting seats and the second spring mounting seats are all fitted with springs on their exteriors. By adopting the above technical solution, the spring can reduce the vibration amplitude of the lower support frame when the upper support frame vibrates after the first and second vibration motors start, thereby ensuring the stable operation of the entire equipment.
[0010] Preferably, a controller mounting bracket is fixedly installed on one side of the lower support frame, and a controller is fixedly installed inside the controller mounting bracket. The controller is electrically connected to the first motor, the second motor, the first electric cylinder, the second electric cylinder, the first vibration motor, and the second vibration motor. By adopting the above technical solution, the controller is used to control the start-stop and running power of the first motor, the second motor, the first electric cylinder, the second electric cylinder, the first vibration motor, and the second vibration motor.
[0011] Preferably, upper fixing plates are fixedly installed on both sides of the upper support frame, and lower fixing plates corresponding to the upper fixing plates are fixedly installed on both sides of the lower support frame. Bolts are slidably installed inside the lower fixing plates, and the upper ends of the bolts pass through the upper fixing plates and are threaded with nuts. By adopting the above technical solution, the upper fixed plate and the lower fixed plate are connected by bolts and nuts, which can ensure the stability of the upper support frame during transportation and avoid the vibration of the lower support frame during transportation, which would cause greater vibration of the upper support frame and the structure installed on the upper support frame through the transmission of springs. Beneficial effects
[0012] In summary, this application includes at least one of the following beneficial technical effects: This invention provides a wing performance testing device. A connecting plate is provided on one side of a movable plate. A first electric cylinder is mounted on the lower side of a mounting plate via a first electric cylinder mounting bracket. The telescopic end of the first electric cylinder is fixedly connected to the surface of the connecting plate. A first vibration motor and a second vibration motor are provided at the lower end of the mounting plate, and the first and second vibration motors are distributed at a perpendicular angle. Two second slide rails are provided on the upper part of the movable plate, and two second sliders are slidably fitted at both ends of each of the two second slide rails. A connecting seat is rotatably mounted on the upper end of each second slider via a fixed plate. Two corresponding connecting seats are respectively fixedly mounted on mounting boxes. A second electric cylinder is also mounted on the lower end of the mounting plate via a second electric cylinder mounting bracket. A rotating seat is provided on the lower end of one of the two carrier plates corresponding to the second electric cylinder. The telescopic end of the second electric cylinder is rotatably connected to the rotating seat. In use, the wing is installed inside the two mounting boxes, and then the second electric cylinder is activated. The extension and retraction of the second electric cylinder causes the carrier plate with the rotating seat to move and change its angle. Because the two carrier plates are connected by a hinge, the angle of the other carrier plate will change simultaneously, thereby changing the angle between the two wings and simulating different wing mounting angles. Then, the controller starts the first and second vibration motors. The first and second vibration motors are distributed at a perpendicular angle to simulate vibrations at different angles, thus more realistically simulating the actual flight state of the wing and improving experimental accuracy. At the same time, the first electric cylinder is started, and its extension and retraction causes the connecting plate to move, which in turn causes the moving plate to move, which in turn causes the carrier plate, mounting box, and wings to move, thus simulating the pitch motion of the wing during flight. Therefore, during use, it can accurately reproduce the comprehensive test of the wing in static, dynamic, and complex environments, covering most typical working conditions in wing flight, making the test results closer to actual performance.
[0013] This invention provides a wing performance testing device. It comprises a first bidirectional lead screw with first slides mounted on both ends. First mounting seats are mounted on the upper ends of the two first slides. A first motor is fixedly connected to one end of the first bidirectional lead screw at one end of the mounting box. Second slides are mounted on both ends of the second bidirectional lead screw, with second mounting seats mounted on the upper ends of each second slide. A second motor is located on one side of the mounting box, with its output fixedly connected to one end of the second bidirectional lead screw. In use, activating the first motor rotates the first bidirectional lead screw, causing the two first slides and the first mounting seats to move towards or away from each other, thus changing the distance between the two first mounting seats. Activating the second motor rotates the second bidirectional lead screw, causing the two second slides and the second mounting seats to move towards or away from each other, thus changing the distance between the two second mounting seats. This device is suitable for wing installations of different specifications, thus broadening its applicability. Attached Figure Description
[0014] Figure 1 This is a schematic diagram of the overall structure of the present invention; Figure 2 This is a schematic diagram of the mounting structure of the first and second vibration motors of the present invention; Figure 3 This is a schematic diagram of the mounting structure of the first and second electric cylinders of the present invention; Figure 4 This is a schematic diagram of the mounting structure of the first and second mounting bases of the present invention; Figure 5 for Figure 1 Enlarged view of the structure at point A in the middle.
[0015] The components include: 1. Upper support frame; 2. Lower support frame; 3. Mounting plate; 4. First slide rail; 5. First slider; 6. Mounting block; 7. Moving plate; 8. First electric cylinder mounting bracket; 9. Connecting plate; 10. First electric cylinder; 11. Second slide rail; 12. Second slider; 13. Fixing plate; 14. Connecting seat; 15. Mounting box; 16. First double-acting lead screw; 17. First motor; 18. First guide rod; 19. First slide table; 20. First mounting seat; 21. Second double-acting lead screw; 22. Second motor. ; 23. Second guide rod; 24. Second slide; 25. Second mounting base; 26. Carrier plate; 27. First vibration motor; 28. Second vibration motor; 29. Second electric cylinder mounting bracket; 30. Second electric cylinder; 31. Rotating seat; 32. Hinge; 33. Through hole; 34. First spring mounting base; 35. Second spring mounting base; 36. Spring; 37. Controller mounting bracket; 38. Controller; 39. Lower fixing plate; 40. Upper fixing plate; 41. Bolt; 42. Nut; 43. Support leg. Detailed Implementation
[0016] The following is in conjunction with the appendix Figure 1 - Appendix Figure 5 This application will be described in further detail below.
[0017] Example 1: A wing performance testing device includes an upper support frame 1 and a lower support frame 2. A mounting plate 3 is fixedly mounted on the upper end of the upper support frame 1. A first vibration motor 27 is fixedly mounted on the lower end of the mounting plate 3. A second vibration motor 28 is fixedly mounted on the lower end of the mounting plate 3 near the first vibration motor 27. The first vibration motor 27 and the second vibration motor 28 are distributed at a perpendicular angle. First slide rails 4 are fixedly mounted on both sides of the upper end of the mounting plate 3. Two first sliders 5 are slidably mounted on the outside of each of the two first slide rails 4. Each of the two first sliders 5 has a fixed upper end... Mounting block 6, a movable plate 7 is fixedly installed between two mounting blocks 6, a second slide rail 11 is fixedly installed on both sides of the upper end of the movable plate 7, a second slider 12 is slidably installed on the outer sides of both sides of the two second slide rails 11, a fixed plate 13 is fixedly installed on the upper end of each of the four second sliders 12, a connecting seat 14 is rotatably installed on the upper end of each of the four fixed plates 13, a carrier plate 26 is fixedly installed on each of the two corresponding connecting seats 14, a hinge 32 is installed between the two carrier plates 26, and a mounting box 15 is fixedly installed on the upper end of each of the two carrier plates 26; Both mounting boxes 15 have a first bidirectional lead screw 16 rotatably mounted inside. Each end of the first bidirectional lead screw 16 is threaded with a first slide 19. A first mounting base 20 is fixedly mounted on the upper end of each of the two slides 19. Inside the mounting box 15, on both sides of the first bidirectional lead screw 16, first guide rods 18 are fixedly mounted, and both guide rods 18 are slidably connected to the first slides 19. A first motor 17 is fixedly mounted on one end of the mounting box 15, and the output end of the first motor 17 is fixedly connected to one end of the first bidirectional lead screw 16. When in use, starting the first motor 17 drives the first bidirectional lead screw 16 to rotate. The rotation of the first bidirectional lead screw 16 causes the two first slides 19 and the first mounting base 20 to move in opposite directions, thereby changing the position of the two first mounting bases 20. The mounting box 15 has a 0-degree gap. Inside the mounting box 15, a second bidirectional lead screw 21 is rotatably installed. Both ends of the second bidirectional lead screw 21 are threaded with second slides 24. The upper ends of the two slides 24 are fixedly provided with second mounting seats 25. Inside the mounting box 15, on both sides of the second bidirectional lead screw 21, second guide rods 23 are fixedly provided. The two guide rods 23 are slidably connected to the two slides 24. A second motor 22 is fixedly installed on one side of the mounting box 15. The output end of the second motor 22 is fixedly connected to one end of the second bidirectional lead screw 21. When in use, the second motor 22 is started, which drives the second bidirectional lead screw 21 to rotate, thereby causing the two slides 24 and the second mounting seats 25 to move in opposite directions or in the opposite direction, thereby changing the gap between the two second mounting seats 25. A first electric cylinder mounting bracket 8 is fixedly installed on one side of the lower end of the mounting plate 3. A first electric cylinder 10 is fixedly installed at the lower end of the first electric cylinder mounting bracket 8. A connecting plate 9 is fixedly installed on one side of the moving plate 7. The telescopic end of the first electric cylinder 10 is fixedly connected to the surface of the connecting plate 9. When the first electric cylinder 10 is started, its telescopic movement will drive the connecting plate 9 to move, thereby causing the moving plate 7 to swing. A second electric cylinder mounting bracket 29 is fixedly installed at the lower end of the mounting plate 3. A second electric cylinder 30 is fixedly installed at the lower end of the second electric cylinder mounting bracket 29. A rotating seat 31 is fixedly installed at the lower end of the two carrier plates 26 corresponding to the position of the second electric cylinder 30. Both the mounting plate 3 and the moving plate 7 have through holes 33. The telescopic end of the second electric cylinder 30 passes through the two through holes 33 and is rotatably connected to the rotating seat 31. After the second electric cylinder 30 is started, it will drive the carrier plate 26 to move. Because the two carrier plates 26 are connected by a hinge 32, the angle of the two carrier plates 26 will change during the movement. Four first spring mounting seats 34 arranged in a matrix array are fixedly installed at the lower end of the upper support frame 1. Four support legs 43 arranged in a matrix array are fixedly installed at the lower end of the lower support frame 2. Four second spring mounting seats 35 arranged in a matrix array are fixedly installed at the upper end of the lower support frame 2. The four second spring mounting seats 35 correspond to the four first spring mounting seats 34 respectively. The first spring mounting seats 34 and the second spring mounting seats 35 are all fitted with springs 36. The springs 36 can reduce the vibration amplitude of the lower support frame 2 when the first vibration motor 27 and the second vibration motor 28 drive the upper support frame 1 to vibrate, thereby ensuring the stable operation of the entire equipment. A controller mounting frame 37 is fixedly installed on one side of the lower support frame 2. A controller 38 is fixedly installed inside the controller mounting frame 37. The controller 38 is connected to the first motor 17, the second motor 22 and the first electric cylinder 10 respectively. The second electric cylinder 30 is electrically connected to the first vibration motor 27 and the second vibration motor 28. The controller is used to control the start-stop and operating power of the first motor 17, the second motor 22, the first electric cylinder 10, the second electric cylinder 30, the first vibration motor 27, and the second vibration motor 28. The upper support frame 1 is fixedly provided with upper fixing plates 40 on both sides, and the lower support frame 2 is fixedly provided with lower fixing plates 39 corresponding to the upper fixing plates 40 on both sides. Bolts 41 are slidably provided inside the lower fixing plates 39. The upper end of the bolts 41 passes through the upper fixing plates 40 and is threaded with nuts 42. The upper fixing plates 40 and the lower fixing plates 39 are connected by bolts 41 and nuts 42. During transportation, the stability of the upper support frame 1 can be guaranteed, and the vibration of the lower support frame 2 during transportation can be avoided. The upper support frame 1 and the structure installed on the upper support frame 1 will vibrate more significantly through the transmission of spring 36.
[0018] The implementation principle of this application embodiment is as follows: First, according to the specifications of the wing, the first motor 17 is started. The first motor 17 drives the first bidirectional lead screw 16 to rotate, thereby driving the two first slides 19 and the first mounting base 20 to move towards or in opposite directions until the spacing matches the specifications of the wing. Then, the second motor 22 is started. The second motor 22 drives the second bidirectional lead screw 21 to rotate, thereby driving the two second slides 24 and the second mounting base 25 to move towards or in opposite directions until the spacing matches the specifications of the wing. Then, the wing is fixed to the two first mounting bases 20 and the second mounting base 25. Then, the second electric cylinder 30 is activated. The telescopic end of the second electric cylinder 30 drives the corresponding carrier plate 26 to move through the rotating seat 31. Since the two carrier plates 26 are connected by the hinge 32, when one carrier plate 26 moves, it will drive the other carrier plate 26 to rotate synchronously through the hinge 32. At the same time, the carrier plate 26 is rotatably connected to the fixed plate 13 through the connecting seat 14. Through the cooperation of the second slider 12 and the second slide rail 11, the angle of the two carrier plates 26 will change while moving until the two carrier plates 26 reach the preset installation angle, thus simulating the installation angle of the wing. Then, the first electric cylinder 10 is activated. The telescopic end of the first electric cylinder 10 drives the moving plate 7 to move through the connecting plate 9. Then, the moving plate 7 will synchronously drive the upper carrier plate 26, the mounting box 15 and the wing to move, thereby simulating the pitch motion of the wing during flight. The first vibration motor 27 and the second vibration motor 28 are activated synchronously. The two motors are distributed at a vertical angle. After activation, they can form multi-directional vibration to simulate the airflow disturbance encountered by the wing during flight.
Claims
1. A wing performance test device comprising an upper support frame (1) and a lower support frame (2), characterized in that: The upper support frame (1) is fixedly provided with a mounting plate (3) at the upper end, a first vibration motor (27) is fixedly arranged at the lower end of the mounting plate (3), a second vibration motor (28) is fixedly arranged at the position close to the first vibration motor (27) at the lower end of the mounting plate (3), the first vibration motor (27) and the second vibration motor (28) are distributed at a vertical angle, first sliding rails (4) are fixedly arranged at both sides of the upper end of the mounting plate (3), two first sliding blocks (5) are slidingly arranged outside the two first sliding rails (4), mounting blocks (6) are fixedly arranged at the upper end of the two first sliding blocks (5), a moving plate (7) is fixedly arranged between the two mounting blocks (6), second sliding rails (11) are fixedly arranged at both sides of the upper end of the moving plate (7), second sliding blocks (12) are slidingly arranged outside both sides of the two second sliding rails (11), fixed plates (13) are fixedly arranged at the upper end of the four second sliding blocks (12), connecting seats (14) are rotatably arranged at the upper end of the four fixed plates (13), load plates (26) are fixedly arranged in the corresponding two connecting seats (14) among the four connecting seats (14), hinges (32) are arranged between the two load plates (26), and mounting boxes (15) are fixedly arranged at the upper end of the two load plates (26).
2. A wing performance testing device according to claim 1, wherein: First bidirectional screws (16) are rotatably arranged inside the two mounting boxes (15), first sliding tables (19) are threadedly arranged outside the two ends of the first bidirectional screws (16), first mounting seats (20) are fixedly arranged at the upper end of the two first sliding tables (19), first guide rods (18) are fixedly arranged inside the mounting box (15) at both sides of the first bidirectional screw (16), the two first guide rods (18) are slidingly connected with the first sliding table (19), and a first motor (17) is fixedly arranged at one end of the mounting box (15).
3. A wing performance testing apparatus as claimed in claim 2, wherein: Second bidirectional screws (21) are rotatably arranged inside the mounting box (15), second sliding tables (24) are threadedly arranged at both ends of the second bidirectional screws (21), second mounting seats (25) are fixedly arranged at the upper end of the two second sliding tables (24), second guide rods (23) are fixedly arranged inside the mounting box (15) at both sides of the second bidirectional screw (21), the two second guide rods (23) are slidingly connected with the two second sliding tables (24), and a second motor (22) is fixedly arranged at one side of the mounting box (15).
4. The wing performance test apparatus according to claim 1, characterized by: A first electric cylinder mounting frame (8) is fixedly arranged at one side of the lower end of the mounting plate (3), a first electric cylinder (10) is fixedly arranged at the lower end of the first electric cylinder mounting frame (8), a connecting plate (9) is fixedly arranged at one side of the moving plate (7), and the telescopic end of the first electric cylinder (10) is fixedly connected with the surface of the connecting plate (9).
5. The wing performance test apparatus according to claim 1, characterized by: The lower end of the mounting plate (3) is fixedly provided with a second electric cylinder mounting rack (29), the lower end of the second electric cylinder mounting rack (29) is fixedly provided with a second electric cylinder (30), the lower end of the load plate (26) corresponding to the position of the second electric cylinder (30) is fixedly provided with a rotating seat (31), the mounting plate (3) and the moving plate (7) are both provided with through holes (33), and the telescopic end of the second electric cylinder (30) penetrates the two through holes (33) and is rotationally connected with the rotating seat (31).
6. The wing performance test apparatus of claim 1, wherein: The lower end of the upper support frame (1) is fixedly provided with four first spring mounting seats (34) arranged in a matrix array, the lower end of the lower support frame (2) is fixedly provided with four supporting legs (43) arranged in a matrix array, the upper end of the lower support frame (2) is fixedly provided with four second spring mounting seats (35) arranged in a matrix array, the four second spring mounting seats (35) correspond to the positions of the four first spring mounting seats (34) respectively, and the first spring mounting seat (34) and the second spring mounting seat (35) are jointly sleeved with a spring (36) outside.
7. The wing performance testing apparatus of claim 1, wherein: One side of the lower support frame (2) is fixedly provided with a controller mounting rack (37), the inside of the controller mounting rack (37) is fixedly provided with a controller (38), and the controller (38) is electrically connected between the first motor (17), the second motor (22) and the first electric cylinder (10), the second electric cylinder (30), and the first vibration motor (27) and the second vibration motor (28) respectively.
8. The wing performance testing apparatus of claim 1, wherein: Both sides of the upper support frame (1) are fixedly provided with upper fixed plates (40), both sides of the lower support frame (2) are fixedly provided with lower fixed plates (39) corresponding to the upper fixed plates (40), the inside of the lower fixed plate (39) is slidably provided with a bolt (41), the upper end of the bolt (41) penetrates the upper fixed plate (40) and is threadedly sleeved with a nut (42).