Aircraft skin installing and riveting tool

Abstract

The utility model discloses an aircraft skin installing and riveting tool and belongs to the technical field of aircraft manufacturing. The upper end of the vehicle body is fixedly connected with the fixed end of the electric telescopic rod, the telescopic end of the electric telescopic rod is fixedly connected with the fixed frame, the two sides of the upper end of the fixed frame are provided with the unfolding mechanisms, the two unfolding mechanisms are symmetrically arranged, the fixed seat is arranged between the two unfolding mechanisms and fixedly connected with the fixed frame, and the upper end of the fixed seat is provided with a first sliding groove; the first sliding grooves are in sliding connection with the first sliding rods, the first sliding rods are fixedly connected with the top plate, the first sliding rods are sleeved with the second springs, one ends of the second springs are fixedly connected with the fixing base, the other ends of the second springs are fixedly connected with the top plate, the multiple second sliding grooves are formed in the upper end of the top plate in an array mode, and a telescopic mechanism is arranged in each second sliding groove. By means of the advantages of being high in self-adaptability and stability, improving riveting efficiency and quality, being easy and convenient to operate and the like, powerful support is provided for installation and riveting work of the aircraft skin, and working efficiency and quality are greatly improved.

Description

Technical Field

[0001] This utility model belongs to the field of aircraft manufacturing technology, specifically an aircraft skin installation and riveting fixture. Background Technology

[0002] In the aircraft manufacturing industry, the installation of the skin is a crucial step, directly affecting the aircraft's aerodynamic performance, structural strength, and flight safety. In particular, the skin located under the aircraft needs to be precisely fitted to the airframe structure during installation and fixed by means of riveting and other connection methods. During this process, it is necessary to ensure the stable support and precise positioning of the skin.

[0003] Traditional aircraft skin installation methods often rely on manual hand-held or simple tooling for support and positioning. While these methods can meet installation requirements to some extent, they have several shortcomings. First, manual hand-held support often fails to guarantee the stability and installation accuracy of the skin, and is easily affected by the operator's skill level and physical condition. Second, although simple tooling can provide support to some extent, its adaptability and flexibility are poor, making it difficult to meet the installation requirements of different aircraft skin models and shapes. Utility Model Content

[0004] To address the problems existing in the background technology, this utility model provides an aircraft skin mounting and riveting fixture.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: an aircraft skin installation and riveting fixture, comprising a vehicle body, an electric telescopic rod, a fixing frame, a fixing seat, a sliding rod one, a spring two, a top plate, two unfolding mechanisms and multiple telescopic mechanisms;

[0006] The upper end of the vehicle body is fixedly connected to the fixed end of the electric telescopic rod, and the telescopic end of the electric telescopic rod is fixedly connected to the fixed frame. The upper end of the fixed frame is provided with an unfolding mechanism on both sides. The two unfolding mechanisms are symmetrically arranged, and a fixed seat is provided between the two unfolding mechanisms. The fixed seat is fixedly connected to the fixed frame. The upper end of the fixed seat is provided with a sliding groove, which is slidably connected to a sliding rod. The sliding rod is fixedly connected to the top plate. A second spring is fitted on the sliding rod. One end of the second spring is fixedly connected to the fixed seat, and the other end of the second spring is fixedly connected to the top plate. The upper end of the top plate is provided with multiple sliding grooves, and each sliding groove is provided with a telescopic mechanism.

[0007] Each of the aforementioned deployment mechanisms includes an arc-shaped slide bar, a spring, a support plate, and a rubber roller;

[0008] One end of the arc-shaped slide rod is fixedly connected to the fixed frame. The support plate is provided with a sliding hole. The other end of the arc-shaped slide rod slides through the sliding hole and is provided with a limiting boss. A spring is fitted on the arc-shaped slide rod. One end of the spring is fixedly connected to the fixed frame, and the other end of the spring is fixedly connected to the support plate. The lower end of the support plate is hinged to the fixed frame. The rubber roller is rotatably connected to the upper end of the support plate.

[0009] Each of the telescopic mechanisms includes a fixed column, a second sliding rod, a third spring, and a rubber head;

[0010] The lower end of the fixed column is fixedly connected to the bottom end of the corresponding sliding groove two. The lower end of the sliding rod two is provided with a sliding groove three, which is slidably connected to the upper end of the fixed column. The spring three is fitted on the fixed column. One end of the spring three is fixedly connected to the sliding rod two, and the other end of the spring three is fixedly connected to the bottom end of the corresponding sliding groove two. The upper end of the sliding rod two is fixedly connected to the rubber head.

[0011] Compared with the prior art, the beneficial effects of this utility model are:

[0012] 1. High Adaptability: The tooling is driven to rise by an electric telescopic rod, allowing the deployment and telescopic mechanisms to gradually contact the aircraft skin and adapt to its shape. The rubber rollers and springs in the deployment mechanism allow the tooling to adapt to the curvature under the aircraft, ensuring that the rubber rollers are always in close contact with the skin, providing the necessary support and adaptability. The telescopic mechanism has the ability to selectively retract, adjusting according to the local curvature of the skin to ensure that the tooling fits tightly against the surface of the skin, regardless of its shape.

[0013] 2. High stability: The combination design of the top plate, slide bar, and spring ensures that the tooling remains stable when subjected to the reaction force of the skin and will not easily shift due to external forces. The rebound effect of the spring not only provides additional support but also ensures the stability of the tooling during the process of tightly fitting with the skin.

[0014] 3. Improved riveting efficiency and quality: The tooling can fit tightly against the surface of the skin and adapt to its shape changes, ensuring the accuracy of the riveting work; due to the high adaptability and stability of the tooling, riveting errors or quality problems caused by the tooling not fitting tightly against the skin are reduced, thus improving the efficiency and quality of the riveting work.

[0015] 4. Easy to operate: The tooling design makes the operation process simple and easy. Just move the tooling to the predetermined position and start the electric telescopic rod to automatically complete the fitting process with the skin; the adaptive design of the unfolding mechanism and the telescopic mechanism reduces the need for manual adjustment and improves work efficiency.

[0016] In summary, this utility model, with its advantages of high adaptability, stability, improved riveting efficiency and quality, and ease of operation, provides strong support for the installation and riveting of aircraft skin, greatly improving work efficiency and quality. Attached Figure Description

[0017] Figure 1 This is a front view of the present invention;

[0018] Figure 2 yes Figure 1 A magnified view of part A. Detailed Implementation

[0019] The technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments of this utility model. Obviously, the described embodiments are only some embodiments of the utility model, not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this utility model without creative effort are within the protection scope of this utility model.

[0020] This embodiment describes an aircraft skin installation and riveting fixture, including a vehicle body 1, an electric telescopic rod 2, a fixing frame 3, a fixing seat 8, a sliding rod 9, a spring 10, a top plate 11, two unfolding mechanisms, and multiple telescopic mechanisms.

[0021] The upper end of the vehicle body 1 is fixedly connected to the fixed end of the electric telescopic rod 2. The telescopic end of the electric telescopic rod 2 is fixedly connected to the fixed frame 3. The fixed frame 3 has an unfolding mechanism on both sides of its upper end. The two unfolding mechanisms are symmetrically arranged. A fixed seat 8 is provided between the two unfolding mechanisms. The fixed seat 8 is fixedly connected to the fixed frame 3. The upper end of the fixed seat 8 is provided with a sliding groove 1. The sliding groove 1 is slidably connected to a sliding rod 9. The sliding rod 9 is fixedly connected to the top plate 11. A spring 2 10 is fitted on the sliding rod 9. One end of the spring 2 10 is fixedly connected to the fixed seat 8. The other end of the spring 2 10 is fixedly connected to the top plate 11. The upper end of the top plate 11 is provided with a plurality of sliding grooves 2 in an array. Each sliding groove 2 is provided with a telescopic mechanism.

[0022] Each of the aforementioned deployment mechanisms includes an arc-shaped slide bar 4, a spring 5, a support plate 6, and a rubber roller 7;

[0023] One end of the arc-shaped slide rod 4 is fixedly connected to the fixed frame 3. The support plate 6 is provided with a sliding hole. The other end of the arc-shaped slide rod 4 slides through the sliding hole and is provided with a limiting boss. The spring 5 is fitted on the arc-shaped slide rod 4. One end of the spring 5 is fixedly connected to the fixed frame 3, and the other end of the spring 5 is fixedly connected to the support plate 6. The lower end of the support plate 6 is hinged to the fixed frame 3. The rubber roller 7 is rotatably connected to the upper end of the support plate 6.

[0024] Each of the telescopic mechanisms includes a fixed column 12, a slide bar 13, a spring 14, and a rubber head 15;

[0025] The lower end of the fixed column 12 is fixedly connected to the bottom end of the corresponding sliding groove 2. The lower end of the sliding rod 2 13 is provided with a sliding groove 3, which is slidably connected to the upper end of the fixed column 12. The spring 3 14 is fitted on the fixed column 12. One end of the spring 3 14 is fixedly connected to the sliding rod 2 13, and the other end of the spring 3 14 is fixedly connected to the bottom end of the corresponding sliding groove 2. The upper end of the sliding rod 2 13 is fixedly connected to the rubber head 15.

[0026] When using this utility model, firstly, move the vehicle body 1 of the tooling to the predetermined position for installing the skin under the aircraft, and ensure that the skin is accurately placed in the preset installation position and aligned with the tooling. Then, start the electric telescopic rod 2, and its telescopic end begins to drive the fixing frame 3 to slowly rise. As the fixing frame 3 rises, the two unfolding mechanisms located at its upper end first contact the skin. These two unfolding mechanisms are symmetrically arranged and can adapt to the curvature under the aircraft. When the rubber rollers 7 are in contact with the outer wall of the skin, they will unfold to both sides according to the curvature of the skin. The rebound action of spring 5 ensures that the rubber rollers 7 are always tightly attached to the skin, providing necessary support and adaptability. As the fixing frame 3 continues to rise, multiple arrayed telescopic mechanisms also gradually contact the outer wall of the skin. These telescopic mechanisms have the ability to selectively retract and can be adjusted according to the local curvature of the skin. Specifically, slide rod 13 in The tool slides within the second groove, compressing the third spring 14 to adapt to the shape and curvature of the skin. This design allows the tooling to fit tightly against the surface of the skin, regardless of its shape. When the mounting bracket 3 rises to a certain extent, the top plate 11 is subjected to the reaction force of the skin, which begins to press down on the first slide rod 9. The first slide rod 9 moves into the mounting base 8 within the first groove, while the second spring 10 is compressed. During this process, the second spring 10 provides additional support force, ensuring that the top plate 11 and the entire device maintain a stable support state when subjected to the reaction force. Finally, once the tooling is tightly fitted and stable against the skin, the riveting work of the skin can begin. Because the tooling has good adaptability and stability, it can fit tightly against the surface of the skin and adapt to its shape changes, thus ensuring the accuracy and efficiency of the riveting work. This design greatly improves the efficiency and quality of aircraft skin installation and riveting.

[0027] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of the equivalents of the claims are intended to be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. An aircraft skin installation riveting tool characterized by: Including the car body (1), electric telescopic rod (2), fixed frame (3), fixed seat (8), slide bar one (9), spring two (10), top plate (11), two unfolding mechanisms and multiple telescopic mechanisms; The upper end of the car body (1) is fixedly connected with the fixed end of the electric telescopic rod (2), the telescopic end of the electric telescopic rod (2) is fixedly connected with the fixed frame (3), the upper end of the fixed frame (3) is provided with an unfolding mechanism on each side, the two unfolding mechanisms are symmetrically arranged, a fixed seat (8) is arranged between the two unfolding mechanisms, the fixed seat (8) is fixedly connected with the fixed frame (3), the upper end of the fixed seat (8) is provided with a sliding groove one, the sliding groove one is slidably connected with the slide bar one (9), the slide bar one (9) is fixedly connected with the top plate (11), the spring two (10) is sleeved on the slide bar one (9), one end of the spring two (10) is fixedly connected with the fixed seat (8), the other end of the spring two (10) is fixedly connected with the top plate (11), and the upper end of the top plate (11) is arrayed with multiple sliding grooves two, and each sliding groove two is provided with a telescopic mechanism.

2. The riveting tool for installing a skin on an aircraft as defined in claim 1, wherein: Each of the unfolding mechanisms comprises an arc-shaped slide bar (4), a spring one (5), a supporting plate (6) and a rubber roller (7); One end of the arc-shaped slide bar (4) is fixedly connected with the fixed frame (3), the supporting plate (6) is provided with a sliding hole, the other end of the arc-shaped slide bar (4) is slidably connected through the sliding hole and is provided with a limiting boss, the spring one (5) is sleeved on the arc-shaped slide bar (4), one end of the spring one (5) is fixedly connected with the fixed frame (3), the other end of the spring one (5) is fixedly connected with the supporting plate (6), and the lower end of the supporting plate (6) is hingedly connected with the fixed frame (3), and the rubber roller (7) is rotatably connected with the upper end of the supporting plate (6).

3. The riveting tool of claim 1 wherein: Each of the telescopic mechanisms comprises a fixed column (12), a slide bar two (13), a spring three (14) and a rubber head (15); The lower end of the fixed column (12) is fixedly connected with the inner bottom end of the corresponding sliding groove two, the lower end of the slide bar two (13) is provided with a sliding groove three, the sliding groove three is slidably connected with the upper end of the fixed column (12), the spring three (14) is sleeved on the fixed column (12), one end of the spring three (14) is fixedly connected with the slide bar two (13), the other end of the spring three (14) is fixedly connected with the inner bottom end of the corresponding sliding groove two, and the upper end of the slide bar two (13) is fixedly connected with the rubber head (15).

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