Airplane structural member detection clamp
The testing fixture, composed of a support plate, a clamping frame, and a clamping rod, combined with a servo motor and a return spring, solves the problem that existing fixtures are difficult to adapt to new structural components. It achieves flexible and precise clamping, reduces replacement costs and difficulty, and improves testing efficiency.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-19
- Publication Date
- 2026-03-10
AI Technical Summary
Existing aircraft structural component inspection fixtures are difficult to adapt to new structural components with different shapes, resulting in the need for frequent replacement of special fixtures, which increases manufacturing costs and difficulty of use.
The testing fixture, consisting of a support plate, a clamping frame, and a clamping rod, combined with a servo motor and a return spring, achieves flexible and precise clamping adjustment through the rigid support and elastic adaptive characteristics of the moving mechanism and the clamping rod.
It improves the versatility and adaptability of the testing fixture, reduces the cost and difficulty of replacing special fixtures, and improves testing efficiency.
Smart Images
Figure CN223981704U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to the technical field of aircraft manufacturing, specifically to an aircraft structural part detection fixture. BACKGROUND
[0002] As an important part of modern transportation, aircraft plays a crucial role in the fields of aviation transportation, military, scientific research, etc. With the progress of science and technology and the rapid development of the aviation industry, the performance, safety and reliability of aircraft are increasingly demanding. Aircraft structural parts, as the key components of aircraft, directly affect the overall performance and service life of the aircraft. Therefore, during the aircraft manufacturing process, the detection of structural parts is particularly important.
[0003] In the traditional aircraft structural part detection method, manual visual inspection and simple mechanical measurement tools are mainly relied on. Aircraft structural parts are diverse in shape and size, and with the continuous progress of aircraft design, new structural parts are constantly emerging. The existing fixture design is often based on traditional structural part shape and performance requirements, so it is difficult to adapt to the detection needs of these new structural parts, resulting in the need to design special fixtures for different types of structural parts, increasing the manufacturing cost and difficulty of use. Therefore, the technical personnel in the field provide an aircraft structural part detection fixture to solve the problems raised in the background technology. SUMMARY
[0004] The purpose of the utility model is to provide an aircraft structural part detection fixture to solve the problems raised in the background technology.
[0005] To achieve the above purpose, the utility model provides the following technical scheme:
[0006] An aircraft structural part detection fixture comprises:
[0007] A support plate is provided with a first clamping frame at one end, and a second clamping frame is connected to the other end of the support plate through a moving mechanism;
[0008] A plurality of clamping rods are provided with through holes on the first clamping frame and the second clamping frame for the clamping rods to pass through, and connection grooves are provided in the first clamping frame and the second clamping frame. A baffle is installed on one end of the first clamping frame and the second clamping frame through mounting bolts, and a return spring is provided between the baffle and the clamping rod.
[0009] Preferably, the moving mechanism comprises a servo motor, a threaded rod and a moving block, the servo motor is installed at one end of the support plate, a moving groove for the threaded rod to rotate and connect is formed on the support plate, the moving block is threadedly connected with the threaded rod, and the output end of the servo motor is connected with the extension end of the threaded rod penetrating through the moving groove, and the moving block is fixedly connected with the second clamping frame.
[0010] Preferably, first limiting blocks are fixedly arranged at two sides of the second clamping frame, and first limiting grooves for the first limiting blocks to slide and connect are formed on the support plate.
[0011] Preferably, pulleys are installed at lower ends of the first limiting blocks and slide and connect in the first limiting grooves.
[0012] Preferably, second limiting blocks are fixedly arranged at two sides of the clamping rod, and second limiting grooves for the second limiting blocks to slide and connect are formed on the first clamping frame and the second clamping frame.
[0013] Preferably, a rubber head is arranged at one end of the clamping rod away from the reset spring, a connecting ring is arranged at one side of the rubber head, and the connecting ring is sleeved at one end of the clamping rod.
[0014] Preferably, a first connecting column is arranged at one end of the clamping rod away from the rubber head, a second connecting column corresponding to the first connecting column is fixedly arranged on the baffle, and the reset spring is sleeved at the first connecting column and the second connecting column at two ends respectively.
[0015] Compared with the prior art, the device has the advantages that:
[0016] 1. The device is provided with a plurality of clamping rods and reset springs, utilizes the rigid support of the clamping rods and the elastic self-adapting characteristics of the reset springs, can dynamically adjust the clamping state flexibly and accurately according to the changing shape of the aircraft structural member, thereby adapting to the clamping use of the new aircraft structural member, effectively reducing the manufacturing cost caused by frequent replacement of special clamping tooling, and reducing the use difficulty.
[0017] 2. The device is provided with a moving mechanism, can drive the second clamping frame to move, can adjust the distance between the first clamping frame and the second clamping frame according to the size of the aircraft structural member, and improves the universality and adaptability of the equipment. BRIEF DESCRIPTION OF DRAWINGS
[0018] Figure 1 Fig. 1 is a structural schematic view of an aircraft structural member detection clamp in an embodiment of the present application;
[0019] Figure 2 Fig. 2 is a sectional structural schematic view of the aircraft structural member detection clamp in the embodiment of the present application;
[0020] Figure 3 for Figure 2 Enlarged view of point A in the middle;
[0021] Figure 4 This is a cross-sectional view of the second clamping frame of an aircraft structural component inspection fixture according to an embodiment of this application.
[0022] In the diagram: 1. Support plate; 2. First clamping frame; 3. Second clamping frame; 4. Clamping rod; 5. Through hole; 6. Connecting groove; 7. Mounting bolt; 8. Baffle; 9. Return spring; 10. Servo motor; 11. Threaded rod; 12. Moving block; 13. Moving groove; 14. First limiting block; 15. First limiting groove; 16. Pulley; 17. Second limiting block; 18. Second limiting groove; 19. Rubber head; 20. Connecting ring; 21. First connecting post; 22. Second connecting post; 23. Controller. Detailed Implementation
[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.
[0024] Please see Figures 1-4 This utility model provides a technical solution:
[0025] An aircraft structural component inspection fixture, comprising:
[0026] A support plate 1 is provided with a first clamping frame 2 fixed at one end of the support plate 1 and a second clamping frame 3 connected to the other end of the support plate 1 through a moving mechanism. The moving mechanism includes a servo motor 10, a threaded rod 11 and a moving block 12. The servo motor 10 is installed at one end of the support plate 1. A moving groove 13 is provided on the support plate 1 for the threaded rod 11 to rotate and connect. The moving block 12 is threadedly connected to the threaded rod 11, and the output end of the servo motor 10 is connected to the extension end of the threaded rod 11 that passes through the moving groove 13. The moving block 12 is fixedly connected to the second clamping frame 3.
[0027] When adjusting the distance between the first clamping frame 2 and the second clamping frame 3 according to the size of the aircraft structural component, the controller 23 controls the output torque of the servo motor 10. The servo motor 10 drives the moving block 12 to move in the moving groove 13 through the threaded rod 11. Since the moving block 12 is fixedly connected to the second clamping frame 3, it can drive the second clamping frame 3 to move, thereby adjusting the distance between the second clamping frame 3 and the first clamping frame 2, which facilitates the clamping and use of the aircraft structural component.
[0028] Furthermore, the second clamping frame 3 is fixedly provided with first limiting blocks 14 on both sides, and the support plate 1 is provided with a first limiting groove 15 for the first limiting blocks 14 to slide and connect. The lower end of the first limiting block 14 is equipped with a pulley 16, which is slidably connected in the first limiting groove 15.
[0029] When the second clamping frame 3 moves, the first limiting block 14 moves within the first limiting groove 15, which can limit the movement path of the second clamping frame 3. When the first limiting block 14 moves within the first limiting groove 15, the pulley 16 moves within the first limiting groove 15, which can reduce the friction of the first limiting block 14 moving within the first limiting groove 15, thus reducing the load on the servo motor 10.
[0030] A number of clamping rods 4 are provided. The first clamping frame 2 and the second clamping frame 3 are provided with through holes 5 for the clamping rods 4 to pass through. The first clamping frame 2 and the second clamping frame 3 are provided with connecting grooves 6. A baffle 8 is installed at one end of the first clamping frame 2 and the second clamping frame 3 by mounting bolts 7. A return spring 9 is provided between the baffle 8 and the clamping rod 4.
[0031] When clamping aircraft structural components, the second clamping frame 3 moves, and the aircraft structural components press against the clamping rod 4. The clamping rod 4 presses against the return spring 9. The return spring 9 can deform according to the shape of the aircraft structural components. By utilizing the rigid support of the clamping rod 4 and the elastic adaptive characteristics of the return spring 9, it can flexibly and accurately adjust the clamping state dynamically according to the ever-changing shape of the aircraft structural components, thereby adapting to the use of clamping new types of aircraft structural components. This effectively reduces the manufacturing costs caused by frequent replacement of special clamping fixtures and lowers the difficulty of use.
[0032] Furthermore, the clamping rod 4 has a rubber head 19 at the end away from the return spring 9, a connecting ring 20 on one side of the rubber head 19, the connecting ring 20 is sleeved on one end of the clamping rod 4, the clamping rod 4 has a first connecting post 21 at the end away from the rubber head 19, and a corresponding second connecting post 22 is fixed on the baffle 8, and the two ends of the return spring 9 are respectively sleeved on the first connecting post 21 and the second connecting post 22.
[0033] The rubber head 19 increases the friction of the clamping rod 4, improving the clamping effect. The connecting ring 20 facilitates the disassembly and replacement of the rubber head 19. When the spring 9 is damaged due to prolonged use, the mounting bolt 7 can be removed, and the baffle 8 can be taken off. Since the baffle 8 is equipped with a second connecting post 22, one end of the spring 9 is sleeved with the second connecting post 22. Therefore, when the baffle 8 is removed, the second connecting post 22 is removed from one end of the spring 9. Then, the other end of the spring 9 that needs to be replaced is removed from the first connecting post 21, and a new spring 9 can be replaced.
[0034] Based on the above embodiment, a second limiting block 17 is fixedly provided on both sides of the clamping rod 4, and a second limiting groove 18 is provided on the first clamping frame 2 and the second clamping frame 3 for sliding connection of the second limiting block 17.
[0035] When the clamping rod 4 moves to clamp the aircraft structural component, the clamping rod 4 moves within the through hole 5, and at the same time the second limiting block 17 moves within the second limiting groove 18, which can limit the movement path of the clamping rod 4.
[0036] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.
Claims
1. An aircraft structural part inspection fixture, comprising: Include: Supporting plate (1), one end of the supporting plate (1) is fixedly provided with a first clamping frame (2), and the other end of the supporting plate (1) is connected with a second clamping frame (3) through a moving mechanism; A plurality of clamping rods (4), the first clamping frame (2) and the second clamping frame (3) are both provided with through holes (5) for the clamping rods (4) to penetrate, the first clamping frame (2) and the second clamping frame (3) are both provided with connecting grooves (6), the first clamping frame (2) and the second clamping frame (3) are both provided with baffles (8) at one end through mounting bolts (7), and the baffles (8) and the clamping rods (4) are provided with return springs (9) therebetween.
2. An aircraft structural component inspection fixture according to claim 1, wherein: The moving mechanism comprises a servo motor (10), a threaded rod (11) and a moving block (12), the servo motor (10) is installed at one end of the supporting plate (1), the supporting plate (1) is provided with a moving groove (13) for rotatably connecting the threaded rod (11), the moving block (12) is threadedly connected with the threaded rod (11), and the output end of the servo motor (10) is connected with the extension end of the threaded rod (11) penetrating the moving groove (13), and the moving block (12) is fixedly connected with the second clamping frame (3).
3. An aircraft structural component inspection fixture according to claim 2, wherein: The second clamping frame (3) is fixedly provided with first limiting blocks (14) on both sides, and the supporting plate (1) is provided with first limiting grooves (15) for slidably connecting the first limiting blocks (14).
4. An aircraft structural component inspection fixture according to claim 3, wherein: The first limiting blocks (14) are installed with pulleys (16) at the lower ends, and the pulleys (16) are slidably connected in the first limiting grooves (15).
5. The fixture of claim 1, wherein: The clamping rods (4) are fixedly provided with second limiting blocks (17) on both sides, and the first clamping frame (2) and the second clamping frame (3) are both provided with second limiting grooves (18) for slidably connecting the second limiting blocks (17).
6. An aircraft structural component inspection fixture as defined in claim 1, wherein: The clamping rods (4) are provided with rubber heads (19) at one end away from the return springs (9), one side of the rubber head (19) is provided with a connecting ring (20), and the connecting ring (20) is sleeved on one end of the clamping rod (4).
7. An aircraft structural component inspection fixture according to claim 6, wherein: The clamping rods (4) are provided with first connecting columns (21) at one end away from the rubber heads (19), the baffles (8) are fixedly provided with corresponding second connecting columns (22), and the return springs (9) are sleeved on the first connecting columns (21) and the second connecting columns (22) at both ends respectively.