Rotary latch clamp for disassembling aircraft parts

Abstract

The utility model provides a rotary latch clamp for disassembling aircraft parts, which is characterized in that a vertical plate is fixed at the top of a bottom plate through a side plate, a limiting hook plate is fixed on the outer side wall of the upper part of the vertical plate through a clamping side plate, an arc-shaped plate is fixed on the inner side wall of the upper part of the vertical plate, and a rotating plate is hinged to the outer vertex angle part of the arc-shaped plate through a first pin shaft; a rotating power device is mounted between the rotating plate and the arc-shaped plate; the two sides of the top of the rotating plate form a sliding groove through a partition plate and an outer cover plate, an inner sliding plate is installed in the sliding groove in a sliding mode, the end of the inner sliding plate is connected with a locking power device through a self-locking connecting rod mechanism, the locking power device is hinged to the partition plate, an outer sliding plate is fixed to the outer portion of the inner sliding plate, and a locking hook head is fixed to the tail of the outer sliding plate. The clamp can be conveniently and fixedly mounted in a cabin, and is further used for reliably clamping parts in the airplane transformation and disassembly process, so that subsequent operation on the parts can be conveniently carried out by means of a disassembly tool or a repair tool.

Description

Technical Field

[0001] This utility model relates to the field of aircraft modification and dismantling tooling technology, specifically to a rotary latch clamp for dismantling aircraft components. Background Technology

[0002] During the dismantling and modification of the A330 aircraft, our company needs to remove components from the original cabin, such as seats and overhead bins, and enlarge the existing cabin doors. This dismantling and modification process requires frequent component removal for subsequent transport. Reliable clamping and securing of these components is crucial for further dismantling or processing. Currently, there are no dedicated clamping and securing fixtures. Therefore, during dismantling, components must be pre-lifted out of the cabin and then secured using specialized clamping fixtures within the factory, resulting in low dismantling efficiency and high operational difficulty. Utility Model Content

[0003] To address the existing technical problems, the main objective of this utility model is to provide a rotary latching clamp for disassembling aircraft components. This clamp can be easily and securely installed inside the cabin for reliable clamping of components during aircraft modification and disassembly. This allows for subsequent operations on the components using disassembly or repair tools, eliminating the need to transport the components to a factory for clamping and disassembly. This effectively improves disassembly efficiency and ensures disassembly quality.

[0004] To achieve the above-mentioned technical features, the purpose of this utility model is as follows: A rotary latching clamp for disassembling aircraft components includes a base plate, a vertical plate fixed to the top of the base plate via a side plate, a limit hook plate fixed to the upper outer side wall of the vertical plate via a clamping side plate, an arc-shaped plate fixed to the upper inner side wall of the vertical plate, a rotating plate hinged to the outer corner of the arc-shaped plate via a first pin, and a rotational power device installed between the rotating plate and the arc-shaped plate; a sliding groove is formed on both sides of the top of the rotating plate via a partition plate and an outer cover plate, an inner sliding plate is slidably installed inside the sliding groove, the end of the inner sliding plate is connected to the locking power device via a self-locking linkage mechanism, the locking power device is hinged to the partition plate, an outer sliding plate is fixed to the outside of the inner sliding plate, and a locking hook is fixed to the tail of the outer sliding plate.

[0005] Preferably, the base plate is machined with multiple sets of anchor bolt holes for fixed connection with the aircraft floor, and the sides of the anchor bolt holes are provided with waist-shaped bolt holes.

[0006] Preferably, the arc-shaped plate is fixed to the outer wall of the upright plate by multiple sets of first bolt assemblies.

[0007] Preferably, the portion of the upright plate used for mounting the clamping side plate is machined with multiple sets of adjusting bolt holes, and the clamping side plate is fixed by bolt assemblies passing through the adjusting bolt holes.

[0008] Preferably, the rotary power device includes a first cylinder, the base of the first cylinder is hinged to the bottom end of the arc-shaped plate by a second pin, and the top end of the first piston rod of the first cylinder is hinged to the bottom end of the rotating plate by a third pin.

[0009] Preferably, the locking power device includes a second cylinder, the tail of which is hinged to the top of the tail of the partition plate, and the end of the second piston rod of the second cylinder is hinged to a self-locking linkage mechanism.

[0010] Preferably, the self-locking linkage mechanism includes a triangular plate, one of the apex angles of which is hinged to a rotating plate via a pin, the other apex angle of which is hinged to the end of a second piston rod, and the remaining apex angle of which is hinged to a connecting rod, the other end of which is hinged to the end of an inner sliding plate.

[0011] Preferably, one end of the outer sliding plate is machined with a threaded rod, which is connected to the connecting block by a thread. The threaded rod is fixedly connected to the connecting block by a lock nut, and the connecting block is fixedly connected to the inner sliding plate.

[0012] Preferably, the outer cover plate is fixedly connected to the rotating plate by a second bolt assembly.

[0013] Preferably, the tail of the outer sliding plate is connected to the inner sliding plate via a third bolt assembly.

[0014] The present invention has the following beneficial effects:

[0015] 1. This utility model clamp can be easily fixed and installed inside the cabin, and is used for reliable clamping of parts during the aircraft modification and disassembly process, so that the parts can be operated on with disassembly or repair tools without having to transport the parts to the factory for clamping and disassembly. It effectively improves disassembly efficiency and ensures disassembly quality.

[0016] 2. The combination of the above-mentioned anchor bolt holes and waist bolt holes facilitates the fixing of the entire base plate to the floor of the cabin during subsequent use, thereby completing the fixing of the entire fixture.

[0017] 3. The aforementioned arc-shaped plate facilitates a reliable hinged connection to the rotating power device and ensures the reliability of the fixed installation of the arc-shaped plate.

[0018] 4. The aforementioned adjusting bolt holes facilitate subsequent adjustment of the installation height of the clamping side plate, thereby enabling adjustment of the height of the limiting hook plate and ultimately adjusting the distance between the limiting hook plate and the locking hook head. This allows for adaptation to components of different sizes, enhancing the flexibility and reliability of clamping and fixing.

[0019] 5. The aforementioned rotary power device facilitates the provision of power for subsequent rotation.

[0020] 6. The locking power device described above can be used to provide locking power, thereby achieving the locking of the components.

[0021] 7. The self-locking linkage mechanism described above can transmit locking power and achieve a self-locking effect after locking, so as to ensure the reliability of locking.

[0022] 8. The threaded rod facilitates the adjustment of the installation position of the external slide plate, thereby enabling the adjustment of the locking hook position and ensuring that it can be used to lock and fix components of different sizes. Attached Figure Description

[0023] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0024] Figure 1 This is a first-view three-dimensional view of the overall structure of this utility model.

[0025] Figure 2 This is a second-view three-dimensional view of the overall structure of this utility model.

[0026] Figure 3 This is a third-person 3D view of the overall structure of this utility model.

[0027] Figure 4 This is a fourth-view three-dimensional diagram of the overall structure of this utility model.

[0028] Figure 5 This is a fifth-view three-dimensional diagram of the overall structure of this utility model.

[0029] Figure 6 This is the front view of the present utility model.

[0030] Figure 7 This utility model Figure 6 AA view.

[0031] In the diagram: 1. Base plate; 2. Anchor bolt hole; 3. Waist bolt hole; 4. Vertical plate; 5. Side plate; 6. Second pin; 7. First cylinder body; 8. Arc plate; 9. First bolt assembly; 10. First piston rod; 11. Third pin; 12. Second bolt assembly; 13. Clamping side plate; 14. Adjusting bolt hole; 15. Limiting hook plate; 16. Connecting block; 17. Locking nut; 18. Threaded rod; 19. Rotating plate; 20. Triangular plate; 21. Connecting rod; 22. Second piston rod; 23. Inner sliding plate; 24. Slide groove; 25. Spacer plate; 26. Outer cover plate; 27. Second cylinder body; 28. Outer sliding plate; 29. ​​Third bolt assembly; 30. Locking hook head; 31. First pin. Detailed Implementation

[0032] The embodiments of this utility model will be further described below with reference to the accompanying drawings.

[0033] See Figure 1-7 A rotary latching clamp for disassembling aircraft components includes a base plate 1. A vertical plate 4 is fixed to the top of the base plate 1 via a side plate 5. A limiting hook plate 15 is fixed to the upper outer side wall of the vertical plate 4 via a clamping side plate 13. An arc-shaped plate 8 is fixed to the upper inner side wall of the vertical plate 4. A rotating plate 19 is hinged to the outer corner of the arc-shaped plate 8 via a first pin 31. A rotary power device is installed between the rotating plate 19 and the arc-shaped plate 8. The top two sides of the rotating plate 19 form a slide groove 24 via a partition plate 25 and an outer cover plate 26. An inner slide plate 23 is slidably installed inside the slide groove 24. The end of the inner slide plate 23 is connected to the locking power device via a self-locking linkage mechanism. The locking power device is hinged to the partition plate 25. An outer slide plate 28 is fixed to the outside of the inner slide plate 23. A locking hook head 30 is fixed to the tail of the outer slide plate 28. This clamp can be easily and securely installed inside the cabin for reliable clamping of components during aircraft modification and disassembly. This allows for subsequent operations on the components using disassembly or repair tools, eliminating the need to transport the components to a factory for clamping and disassembly. This effectively improves disassembly efficiency and ensures disassembly quality. In practical use, by fixing it inside the cabin, when large components need to be disassembled and clamped, the large component is fixed and supported on the limiting hook plate 15. Then, the corresponding locking power device is activated, which drives the self-locking linkage mechanism, which in turn drives the inner slide plate 23. The inner slide plate 23 then drives the locking hook head 30 to lock and fix the component. When the locking hook head 30 needs to be rotated, a rotation power device is activated, which drives the rotating plate 19 to rotate.

[0034] Furthermore, the base plate 1 is machined with multiple sets of anchor bolt holes 2 for fixed connection with the aircraft floor, and waist-shaped bolt holes 3 are provided on the side of the anchor bolt holes 2. Through the cooperation of the aforementioned anchor bolt holes 2 and waist-shaped bolt holes 3, it is convenient to fix the entire base plate 1 to the cabin floor during subsequent use, thereby completing the fixation of the entire fixture.

[0035] Furthermore, the arc-shaped plate 8 is fixed to the outer wall of the upright plate 4 by multiple sets of first bolt assemblies 9. The arc-shaped plate 8 facilitates a reliable hinged connection to the rotating power device and ensures the reliability of the fixed installation of the arc-shaped plate 8.

[0036] Furthermore, the upright plate 4 has multiple sets of adjusting bolt holes 14 machined on the portion for mounting the clamping side plate 13. The clamping side plate 13 is fixed by bolt assemblies passing through the adjusting bolt holes 14. These adjusting bolt holes 14 facilitate subsequent adjustment of the mounting height of the clamping side plate 13, thereby allowing adjustment of the height of the limiting hook plate 15, and ultimately adjusting the distance between the limiting hook plate 15 and the locking hook head 30. This adapts to components of different sizes, enhancing the flexibility and reliability of the clamping and fixing process.

[0037] Furthermore, the rotary power device includes a first cylinder 7, the base of which is hinged to the bottom end of the arc-shaped plate 8 via a second pin 6. The top end of the first piston rod 10 of the first cylinder 7 is hinged to the bottom end of the rotating plate 19 via a third pin 11. This rotary power device facilitates the provision of power for subsequent rotation. During operation, when the rotating plate 19 needs to be rotated during disassembly, the first cylinder 7 is activated, driving the first piston rod 10, which in turn drives the rotating plate 19 to rotate, causing the plate 19 to rotate around the first pin 31.

[0038] Furthermore, the locking power device includes a second cylinder 27, the tail of which is hinged to the top of the tail of the partition plate 25, and the end of the second piston rod 22 of the second cylinder 27 is hinged to the self-locking linkage mechanism. This locking power device provides locking power to achieve the locking of the component. During operation, when the component needs to be locked, the second cylinder 27 is activated, which drives the second piston rod 22, which in turn drives the self-locking linkage mechanism. The self-locking linkage mechanism then drives the inner slide plate 23 to slide, thereby tightening the locking hook 30.

[0039] Furthermore, the self-locking linkage mechanism includes a triangular plate 20. One apex of the triangular plate 20 is hinged to the rotating plate 19 via a pin, and the other apex of the triangular plate 20 is hinged to the end of the second piston rod 22. The remaining apex of the triangular plate 20 is hinged to a connecting rod 21, and the other end of the connecting rod 21 is hinged to the end of the inner sliding plate 23. This self-locking linkage mechanism can transmit locking power and achieve a self-locking effect after locking, thus ensuring the reliability of the locking.

[0040] Furthermore, a threaded rod 18 is machined at one end of the head of the outer sliding plate 28. The threaded rod 18 is threadedly connected to the connecting block 16, and the threaded rod 18 is fixedly connected to the connecting block 16 by a locking nut 17. The connecting block 16 is fixedly connected to the inner sliding plate 23. The threaded rod 18 facilitates the subsequent adjustment of the installation position of the outer sliding plate 28, thereby realizing the adjustment of the position of the locking hook 30, and ensuring that it can adapt to the locking and fixing of components of different sizes.

[0041] Furthermore, the outer cover plate 26 is fixedly connected to the rotating plate 19 via the second bolt assembly 12. The outer cover plate 26 facilitates its cooperation with the spacer plate 25, thereby forming the sliding groove 24.

[0042] Furthermore, the tail of the outer sliding plate 28 is connected to the inner sliding plate 23 via a third bolt assembly 29. This fixed installation structure ensures a reliable fixed connection between the outer sliding plate 28 and the inner sliding plate 23.

[0043] The working process and principle of this utility model:

[0044] In practical use, the rotary latching clamp described above is used as follows: First, the entire clamp is fixed to the floor of the cabin by anchor bolts passing through the anchor bolt holes 2 and the waist bolt holes 3, thus completing the fixation of the entire clamp. Then, the rotary power device is adjusted as needed. When the rotating plate 19 needs to be rotated during disassembly, the first cylinder 7 is activated, which drives the first piston rod 10, which in turn drives the rotating plate 19 to rotate, and the rotating plate 19 rotates around the first pin 31. The component to be fixed is then supported on the top of the limiting hook plate 15. The second cylinder 27 is activated, which drives the second piston rod 22, which in turn drives the self-locking linkage mechanism, which in turn drives the inner slide plate 23 to slide, thereby achieving the purpose of tightening the locking hook head 30. The locking hook head 30 then clamps the component. After the component is clamped, it is then disassembled and inspected.

Claims

1. A rotary latching clamp for disassembling aircraft components, characterized in that, The base plate (1) is fixed to the top of the base plate (1) by a side plate (5). A limit hook plate (15) is fixed to the upper outer side wall of the base plate (4) by a clamping side plate (13). An arc plate (8) is fixed to the upper inner side wall of the base plate (4). A rotating plate (19) is hinged to the outer corner of the arc plate (8) by a first pin (31). A rotating power device is installed between the rotating plate (19) and the arc plate (8). A slide groove (24) is formed on both sides of the top of the rotating plate (19) by a partition plate (25) and an outer cover plate (26). An inner slide plate (23) is slidably installed inside the slide groove (24). The end of the inner slide plate (23) is connected to the locking power device by a self-locking linkage mechanism. The locking power device is hinged to the partition plate (25). An outer slide plate (28) is fixed to the outside of the inner slide plate (23). A locking hook head (30) is fixed to the tail of the outer slide plate (28).

2. The rotary latch clamp for disassembling aircraft components according to claim 1, characterized in that: The base plate (1) is machined with multiple sets of anchor bolt holes (2) for fixing and connecting with the aircraft floor, and waist-shaped bolt holes (3) are provided on the side of the anchor bolt holes (2).

3. The rotary latch clamp for disassembling aircraft components according to claim 1, characterized in that: The arc-shaped plate (8) is fixed to the outer wall of the upright plate (4) by multiple sets of first bolt assemblies (9).

4. The rotary latch clamp for disassembling aircraft components according to claim 1, characterized in that: The upright plate (4) has multiple sets of adjusting bolt holes (14) for mounting the clamping side plate (13), and the clamping side plate (13) is fixed by bolt assemblies passing through the adjusting bolt holes (14).

5. The rotary latch clamp for disassembling aircraft components according to claim 1, characterized in that: The rotary power device includes a first cylinder (7), the base of the first cylinder (7) is hinged to the bottom end of the arc plate (8) by a second pin (6), and the top end of the first piston rod (10) of the first cylinder (7) is hinged to the bottom end of the rotating plate (19) by a third pin (11).

6. The rotary latch clamp for disassembling aircraft components according to claim 1, characterized in that: The locking power device includes a second cylinder (27), the tail of which is hinged to the top of the tail of the partition plate (25), and the end of the second piston rod (22) of the second cylinder (27) is hinged to the self-locking linkage mechanism.

7. The rotary latch clamp for disassembling aircraft components according to claim 6, characterized in that: The self-locking linkage mechanism includes a triangular plate (20), one of the apex angles of the triangular plate (20) is hinged to the rotating plate (19) by a pin, the other apex angle of the triangular plate (20) is hinged to the end of the second piston rod (22), and the remaining apex angle of the triangular plate (20) is hinged to a connecting rod (21), the other end of the connecting rod (21) is hinged to the end of the inner sliding plate (23).

8. The rotary latch clamp for disassembling aircraft components according to claim 6, characterized in that: The outer sliding plate (28) has a threaded rod (18) machined at one end of its head. The threaded rod (18) is connected to the connecting block (16) by a thread. The threaded rod (18) is fixedly connected to the connecting block (16) by a lock nut (17). The connecting block (16) is fixedly connected to the inner sliding plate (23).

9. A rotary latching fixture for disassembling aircraft components according to claim 6, characterized in that: The outer cover plate (26) is fixedly connected to the rotating plate (19) by the second bolt assembly (12).

10. A rotary latching fixture for disassembling aircraft components according to claim 6, characterized in that: The tail of the outer sliding plate (28) is connected to the inner sliding plate (23) by a third bolt assembly (29).

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