Airplane buckle structure convenient to disassemble and replace

Abstract

The utility model discloses an aircraft buckle structure convenient to disassemble and replace, and relates to the technical field of aircraft buckle structures, the aircraft buckle structure comprises an aircraft buckle structure and a shell mounted on the aircraft buckle structure, a reserved groove is formed in the aircraft buckle structure, the shell is tightly matched in the reserved groove, a ribbon structure is detachably mounted on the shell, and the ribbon structure is detachably mounted on the aircraft buckle structure. The shell is provided with a movable groove for the ribbon structure to slide, and a clamping mechanism used for abutting against or loosening the ribbon structure is arranged in the movable groove. The device has the advantages of being fast to disassemble and assemble, convenient to operate, capable of improving maintenance efficiency and use convenience, capable of being repeatedly used and capable of avoiding waste.

Description

TECHNICAL FIELD

[0001] The application relates to the technical field of aircraft buckle structures, in particular to an aircraft buckle structure convenient to disassemble and replace. BACKGROUND

[0002] As a common fastener, an aircraft buckle is widely used in the fields of automobiles and aviation and is mainly used for quickly connecting and fixing various components. The traditional aircraft buckle is simple and reliable and can effectively meet basic assembly requirements, greatly improving production efficiency and reducing labor intensity.

[0003] In the existing technical means, in order to ensure the safety and reliability of an aircraft or other equipment, an irreversible fixing mode is usually adopted, for example, using glue or welding to permanently fix the aircraft buckle at a specified position. In addition, there are also some detachable designs, such as simple disassembly and assembly through screws or buckles. Although these methods can meet the disassembly and assembly requirements to a certain extent, there are still many inconveniences in actual application. Especially when facing problems such as product size inconsistency and function failure, the above methods often cannot provide effective solutions, resulting in serious resource waste.

[0004] When the aircraft buckle is not suitable in size or is damaged in function, there is a lack of convenient repair means, which not only increases the maintenance cost but also seriously affects the flexibility of production and use. Especially in high-precision application scenarios, once an error occurs, the entire component may need to be scrapped, causing great economic losses. CONTENT OF THE INVENTION

[0005] In order to improve the problem that the traditional aircraft buckle design lacks convenient repair means when encountering size inconsistency and function damage, resulting in the product being unable to be reused and being prone to waste, the application provides an aircraft buckle structure convenient to disassemble and replace.

[0006] The aircraft buckle structure convenient to disassemble and replace provided by the application adopts the following technical scheme:

[0007] The aircraft buckle structure convenient to disassemble and replace comprises an aircraft buckle structure and a shell mounted thereon, a reserved groove is formed in the aircraft buckle structure, the shell is tightly fitted in the reserved groove, a cable tie structure is detachably mounted on the shell, a movable groove for sliding of the cable tie structure is formed in the shell, and a clamping mechanism for clamping or loosening the cable tie structure is arranged in the movable groove.

[0008] By adopting the technical scheme, the aircraft buckle structure has a reserved groove, and when the function of the aircraft buckle fails or the hole diameter is inconsistent, the aircraft buckle structure can be conveniently repaired and replaced, the reusability of the product is improved, and waste is reduced; the shell is tightly fitted in the reserved groove, the stability and reliability of the structure are ensured, the strap structure is detachably installed on the shell, and sliding adjustment is realized through the movable groove, which facilitates the operation of the front-line staff; and the clamping mechanism effectively fixes the strap structure and easily releases the strap structure when needed, thereby further improving the convenience of assembly and maintenance and reducing the damage risk caused by improper operation.

[0009] Optionally, the clamping mechanism includes a pressing needle sliding on the shell, the pressing needle and the strap structure are in clamping connection, and an end of the pressing needle away from the strap structure is provided with a driving piece for driving the pressing needle to move along the axis of the pressing needle.

[0010] By adopting the technical scheme, the aircraft buckle structure can be effectively disassembled and replaced. The clamping mechanism enables the strap structure to be quickly released when needed, thereby avoiding the problem that the traditional aircraft buckle structure cannot be conveniently repaired due to inconsistent hole diameters or function failure; the clamping connection between the pressing needle and the strap structure ensures the stability of the connection; and the driving piece enables the pressing needle to move along the axis of the pressing needle, thereby further improving the convenience and reliability of operation and reducing the damage risk caused by improper disassembly.

[0011] Optionally, the driving piece includes a pull rod fixed on the pressing needle, a spring sleeved on the pull rod, and a limiting ring fixed on the pull rod, a cavity for sliding movement of the limiting ring is formed in the shell, one end of the spring abuts against the inner wall of the cavity, and the other end of the spring abuts against the limiting ring.

[0012] By adopting the technical scheme, the driving piece can effectively realize quick locking and unlocking of the strap structure; the pull rod fixed on the pressing needle and the spring and the limiting ring thereon form an elastic driving system, which can quickly push the pressing needle to move along the axis of the pressing needle under the action of an external force, thereby realizing clamping connection or release of the strap structure; the cavity not only provides a sliding space for the limiting ring but also ensures a reliable working environment for the spring, so that the entire driving process is more stable and controllable, the operation convenience is improved, operation errors of front-line staff in the installation and disassembly process are reduced, product damage caused by frequent disassembly and assembly is avoided, and the service life of the product is prolonged; and the restoring force provided by the spring ensures that the pressing needle is always in a locked state without an external force, thereby enhancing the stability and reliability of the system.

[0013] Optionally, the strap structure includes a strap body sliding in the movable groove and connecting ears fixed on both sides of the strap body, and the connecting ears and the pressing needle are in clamping connection.

[0014] By adopting the technical scheme, detachable connection between the cable tie structure and the shell is realized, the cable tie body slides in the movable slot, the connecting ears on both sides are in clamping cooperation with the abutting needle, the stability and reliability of the cable tie structure in use are ensured, one-line staff can easily press and lift the clamping point, quick disassembly and replacement are realized, damage to the sheath and other accessories in the traditional method is avoided, return repair cost and time are reduced, and production efficiency and product quality are improved.

[0015] Optionally, the aircraft buckle structure comprises a dome-shaped disc mounted on the shell and a buckle head fixed on the dome-shaped disc.

[0016] By adopting the technical scheme, stable connection between the aircraft buckle and the shell is ensured, the stability and reliability of the whole structure are improved, the mechanical strength of the product is improved, the assembly process is facilitated, problems caused by improper assembly are reduced, loosening caused by external impact or vibration is effectively prevented, and the safety and durability of the product in use are improved.

[0017] Optionally, an end of the cable tie body away from the movable slot is chamfered.

[0018] By adopting the technical scheme, one-line staff can easily lift the clamping point in the operation process, prevent the hand from being scratched, and ensure that the clamping point and the cable tie body clamping tooth can be smoothly separated, so that error correction and reuse can be realized at any time.

[0019] Optionally, the pore size of the accommodating cavity is greater than the diameter of the abutting needle, and the length of the accommodating cavity is greater than the length of the abutting needle.

[0020] By adopting the technical scheme, firstly, smooth sliding of the abutting needle in the accommodating cavity is ensured, friction resistance is reduced, and operation convenience is improved, and secondly, enough stroke space of the abutting needle is ensured, so that it can work stably at different positions, and the reliability and durability of the structure are improved.

[0021] Optionally, the caliber of the movable slot is greater than the width of the cable tie body.

[0022] By adopting the technical scheme, smooth sliding of the cable tie body in the movable slot is ensured, clamping or damage caused by too tight size is avoided, assembly efficiency is improved, product damage caused by improper operation is reduced, and the reliability and durability of the product are further improved.

[0023] In summary, the present application has at least one of the following beneficial technical effects:

[0024] 1. By opening a reserved slot on the aircraft buckle structure and installing a shell with a movable slot and a clamping mechanism, convenient disassembly and replacement of the aircraft buckle are realized, and the difficult problem of return repair caused by size inconsistency or functional failure is effectively solved.

[0025] 2. The clamping mechanism enables the cable tie structure to be easily tightened or loosened, avoiding the irreversibility caused by traditional fixing methods, thereby improving product reuse rate and reducing resource waste;

[0026] 3. The cable tie body tail is chamfered, which facilitates the one-line staff to easily pick up the clamping point, avoids the risk of scratching the hand during operation, and ensures that the physical performance of the cable tie itself is not damaged. BRIEF DESCRIPTION OF DRAWINGS

[0027] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed in the embodiment description will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative labor.

[0028] Figure 1 is the overall structure schematic diagram of the aircraft buckle structure shown in the present application.

[0029] Figure 2 is the exploded view of the aircraft buckle structure shown in the present application.

[0030] Figure 3 is the cross-sectional view of the aircraft buckle structure shown in the present application.

[0031] Figure 4 is the A-direction enlarged view of the aircraft buckle structure shown in the present application. Figure 3

[0032] Figure 5 is the B-direction enlarged view of the aircraft buckle structure shown in the present application. Figure 2

[0033] Reference signs: 1, aircraft buckle structure; 2, shell; 3, reserved groove; 4, cable tie structure; 5, movable groove; 6, clamping mechanism; 61, clamping needle; 62, driving piece; 621, pull rod; 622, spring; 623, limiting ring; 624, cavity 41, cable tie body; 42, connecting lug; 11, umbrella-shaped disc; 12, buckle head. DETAILED DESCRIPTION

[0034] The present application will be further described below in combination with the drawings. Figures 1-5

[0035] The embodiment of the present application discloses an aircraft buckle structure convenient to disassemble and replace.

[0036] Referring to Figure 1 and Figure 2 ​​​, including an aircraft buckle structure 1 and a shell 2 mounted thereon, the aircraft buckle structure 1 is provided with a reserved slot 3, the shell 2 is tightly fitted in the reserved slot 3, and the shell 2 is detachably mounted with a strap structure 4, the shell 2 is provided with a movable slot 5 for sliding the strap structure 4, and the movable slot 5 is provided with a clamping mechanism 6 for clamping or loosening the strap structure 4, thereby improving the adaptability and repairability of the aircraft buckle, and solving the problem of lack of convenient repair means when the size of the aircraft buckle does not match or the function is damaged.

[0037] As shown in Figure 2 , the aircraft buckle structure 1 includes a umbrella-shaped disc mounted on the shell 2 and a buckle head fixed on the umbrella-shaped disc, both of which are fixed in a cooperative manner to ensure stable connection and improve the stability and reliability of the entire structure. The buckle head can adopt other shapes such as circular, square or polygonal, depending on the requirements of the actual application scene.

[0038] As shown in Figure 3 and Figure 4 , the clamping mechanism 6 includes a clamping needle 61 sliding on the shell 2, the clamping needle 61 and the strap structure 4 are connected and matched, the end of the clamping needle 61 away from the strap structure 4 is provided with a driving part 62 for driving the clamping needle 61 to move along its own axis, and the head of the clamping needle 61 is conical in shape, which is convenient for inserting into both sides of the strap structure 4.

[0039] As shown in Figure 4 , the driving part 62 includes a pull rod 621 fixed on the clamping needle 61, a spring 622 sleeved on the pull rod 621, and a limiting ring 623 fixed on the pull rod 621, the pull rod 621 is slidingly matched with the shell 2 and the aircraft buckle structure 1, and the limiting ring 623 functions as a limiting part during the movement of the clamping needle 61 to prevent it from overstretching.

[0040] The driving member 62 can effectively realize the quick locking and unlocking of the cable tie structure 4. The pull rod 621 fixed on the abutting needle 61 and the spring 622 and the limiting ring 623 thereon combine to form an elastic driving system, which can quickly push the abutting needle 61 to move along its axis direction under the action of external force, so as to realize the clamping or releasing of the cable tie structure 4. The pull rod 621 pulls the limiting ring 623 to slide in the cavity, and when the spring 622 is compressed by the limiting ring 623, the abutting needle 61 moves to one side of the cable tie structure 4, so that the cable tie structure 4 is convenient to take off from the shell 2. Conversely, under the action of the spring 622, the abutting needle 61 is clamped on both sides of the cable tie structure 4, so that the cable tie structure 4 is clamped in the movable groove 5. The cavity not only provides the sliding space for the limiting ring 623, but also ensures the reliable working environment for the spring 622, so that the whole driving process is more stable and controllable, the operation convenience is improved, the operation errors of the front-line staff in the installation and disassembly process are reduced, the product damage caused by frequent disassembly is avoided, the service life of the product is prolonged, and the stability and reliability of the system are enhanced.

[0041] Referring to Figure 4 As shown in the drawings, the shell 2 is internally provided with a cavity for accommodating the driving member 62 and the limiting ring 623. The aperture of the cavity is larger than the diameter of the abutting needle 61, and the length is larger than the length of the abutting needle 61, so as to facilitate the free sliding of the abutting needle 61. The external surface of the shell 2 is smooth and has no sharp edges, so as to prevent scratching the fingers of the user during use.

[0042] Referring to Figure 4 and Figure 5 As shown in the drawings, the cable tie structure 4 includes a cable tie body sliding in the movable groove 5, and connecting ears fixed on both sides of the cable tie body. The connecting ears and the abutting needle 61 are clamped and matched, realizing the detachable connection between the cable tie structure 4 and the shell 2. The cable tie body slides in the movable groove 5, and the connecting ears on both sides are clamped and matched with the abutting needle 61, ensuring the stability and reliability of the cable tie structure 4 during use, so that the front-line staff can easily press and lift the clamping point to realize quick disassembly and replacement, avoiding the damage to the sheath and other accessories in the traditional method, reducing the repair cost and time, improving the production efficiency and product quality; the end of the cable tie body away from the movable groove 5 is chamfered, so that the front-line staff can not scratch the hand when pressing, and the nail tip can easily lift the clamping point, achieving the effect that the clamping point and the cable tie body are separated.

[0043] The caliber of the movable slot 5 is slightly larger than the width of the cable body, which ensures that the cable body can slide smoothly in the movable slot 5. In addition, in order to prevent the cable structure 4 from being damaged during use, a portion of the upper end of the cable structure 4 can also be extended beyond the sheath cap, with a size of about 1 / 2 of the width of the cable itself, and the tail of the cable is chamfered. In this way, not only can the staff avoid scratching their hands when pressing, but also the nail tip can be used to gently lift the clamping point, achieving the effect of correcting at any time.

[0044] The implementation principle of the aircraft buckle structure 1 according to an embodiment of the present application is that: by providing a reserved slot 3 on the aircraft buckle structure 1 and a detachable cable structure 4 and a clamping mechanism 6 on the shell 2, the convenient disassembly and replacement of the aircraft buckle are achieved. When it is necessary to adjust the position of the aircraft buckle or replace a new aircraft buckle, the cable structure 4 can be easily removed by pressing the abutting needle 61 to make it disengage from the clamping teeth of the cable structure 4, which improves the adaptability and repairability of the aircraft buckle, reduces the waste caused by assembly errors, and saves labor costs.

[0045] Unless otherwise defined, technical terms or scientific terms used in the present application shall be understood as their common meanings to those having ordinary skills in the art to which the present application pertains. The terms "first", "second", "third" and the like used in the specification and claims of the present application do not represent any order, number or importance, but are only used to distinguish different components. The terms "one" or "a" and the like do not represent a quantity limitation, but represent the existence of at least one. The terms "including", "containing" and the like mean that the elements or objects appearing before "including" or "containing" cover the elements or objects listed after "including" or "containing" and their equivalents, and do not exclude other elements or objects. The terms "upper", "lower", "left", "right" and the like are only used to represent relative positional relationships, and when the absolute positions of the described objects change, the relative positional relationships may also change accordingly.

[0046] The above are preferred embodiments of the present application, which do not limit the protection scope of the present application, therefore: any equivalent changes made on the structure, shape, principle of the present application shall be covered within the protection scope of the present application.

Claims

1. A quick-change aircraft fastener structure, comprising: The utility model provides a kind of aircraft buckle structure (1) and shell (2) mounted on it, the aircraft buckle structure (1) is provided with reserved slot (3), the shell (2) is tightly fitted in reserved slot (3), detachably mounted with strap structure (4) on the shell (2), the shell (2) is provided with movable slot (5) for strap structure (4) sliding, movable slot (5) is provided with clamping mechanism (6) for resisting or loosening strap structure (4) in.

2. The aircraft buckle structure of claim 1, wherein: The clamping mechanism (6) includes a resisting needle (61) sliding on the shell (2), the resisting needle (61) and the strap structure (4) are connected, and the end of the resisting needle (61) away from the strap structure (4) is provided with a driving member (62) for driving the resisting needle (61) to move along its own axis.

3. The aircraft buckle structure of claim 2, wherein: The driving member (62) includes a pull rod (621) fixed on the resisting needle (61), a spring (622) sleeved on the pull rod (621), and a limiting ring (623) fixed on the pull rod (621), the shell (2) is internally provided with a cavity for sliding the limiting ring (623), one end of the spring (622) abuts on the inner wall of the cavity, and the other end of the spring (622) abuts on the limiting ring (623).

4. The aircraft fastener structure of claim 3, wherein: The strap structure (4) includes a strap body sliding in the movable slot (5), and connecting ears fixed on both sides of the strap body, the connecting ears and the resisting needle (61) are connected.

5. The aircraft fastener structure of claim 1, wherein: The aircraft buckle structure (1) includes an umbrella-shaped disc mounted on the shell (2) and a buckle head fixed on the umbrella-shaped disc.

6. The aircraft fastener structure of claim 4, wherein: The end of the strap body away from the movable slot (5) is chamfered.

7. The aircraft fastener structure of claim 6, wherein: The aperture of the cavity is larger than the diameter of the resisting needle (61), and the length of the cavity is larger than the length of the resisting needle (61).

8. The aircraft fastener structure of claim 4, wherein: The aperture of the movable slot (5) is larger than the width of the strap body.

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