Airplane vertical tail assembly tool
By designing a vertical tail assembly fixture for aircraft with a limit plate and a rotating frame assembly, the problem of different tail models requiring different fixtures was solved, resulting in material savings, a shorter production cycle, and improved aircraft development efficiency.
Patent Information
- Application Number
- CN202423304111.X
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-31
- Publication Date
- 2025-11-07
- Estimated Expiration
- 2034-12-31
AI Technical Summary
Existing aircraft tail assembly tooling requires the creation of jigs of different sizes depending on the size of the tail, resulting in material waste and extended production preparation cycles, which affects the aircraft development process.
Design a tooling for assembling a vertical tail fin of an aircraft. The tooling uses components such as a limiting plate, a rotating frame, and a telescopic cylinder. The limiting plate fits against the surface of the tail fin to fix different models of tail fins, reducing material waste and improving assembly efficiency.
By combining the limiting plate and the rotating frame, different types of tail fins can be fixed, saving materials, shortening the production preparation cycle, and accelerating the aircraft development process.
Smart Images
Figure CN223521048U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to an aircraft vertical tail assembly technical field, concretely relates to an aircraft vertical tail assembly tool. BACKGROUND
[0002] The aircraft tail assembly is a complicated process, and the technical requirement is relatively high, and thousands of parts need to be accurately positioned and assembled with the tail of the aircraft. The tail of the tool required due to the difference of the aircraft needs to be matched with the tail of the aircraft, so as to be installed.
[0003] At present, when the aircraft tail is assembled, the clamp matched with the tail is needed to assist in installation, and different size clamps need to be made according to the size of different tails, which causes great waste, increases the aircraft manufacturing cost, greatly prolongs the production preparation period of aircraft development, and thus affects the overall development process of aircraft type, therefore, it is particularly important to improve the existing assembly tool and design a new aircraft vertical tail assembly tool to solve the above technical defects and improve the practicability of the overall assembly tool. UTILITY MODEL CONTENT
[0004] The utility model discloses a kind of aircraft vertical tail assembly tools, limit plate is attached to the surface of tail, by the surface of tail of multiple sets of limit plate attachment, tail can be positioned, it is convenient to operate tail, and the rotary connection of first rotary frame and second rotary frame and the sliding connection of limit plate, multiple sets of limit plate can be attached to different models of tail, it is convenient to fix different models of tail, save the material of different types of assembly tool made for different models of tail, improve the aircraft type body development process, to solve the problem proposed in above background technique.
[0005] To achieve the above object, the utility model provides the following technical scheme:
[0006] An aircraft vertical tail assembly tool, including rack main body, the inside of rack main body is slidably connected with moving plate, the top of moving plate is fixedly connected with connecting shell at both ends, and the upper and lower sides of connecting shell are equipped with limiting assembly.
[0007] The limiting assembly is used for limiting tail, and the limiting assembly is composed of first rotary frame, second rotary frame, multiple sets of sleeves, multiple sets of sliding rods and multiple sets of limiting plates.
[0008] As a preferred embodiment of this utility model, the connecting shell has two sets of fixing plates slidably connected inside. The first rotating frame and the second rotating frame are both rotatably connected to the fixing plates, and the two sets of fixing plates are fixedly connected to each other.
[0009] As a preferred embodiment of this utility model, a first telescopic cylinder is fixedly connected to one end of the connecting shell away from the moving plate, and the driving end of the first telescopic cylinder extends into the interior of the connecting shell and is fixedly connected to the connection point of the two sets of fixed plates.
[0010] As a preferred embodiment of this utility model, a first damping spring is fixedly connected to one end of the first rotating frame near the fixed plate, and a support block is fixedly connected to one end of the first rotating frame near the second rotating frame. The support block has a circular structure design.
[0011] As a preferred embodiment of this utility model, the sliding rod extends into the inside of the sleeve and is fixedly connected to a second damping spring, the end of the second damping spring away from the sliding rod being fixedly connected to the sleeve.
[0012] As a preferred embodiment of this utility model, a plurality of friction blocks are fixedly connected to the end of the limiting plate away from the sliding rod. The friction blocks are designed with a semi-circular structure, and the plurality of friction blocks are distributed at equal intervals on the outer side of the limiting plate.
[0013] As a preferred embodiment of this utility model, a connecting frame is fixedly connected inside the movable plate, and the driving end of a second telescopic cylinder is fixedly connected to all four sides of the bottom of the connecting frame. The second telescopic cylinder is fixedly connected inside the main body of the frame.
[0014] Compared with the prior art, the beneficial effects of this utility model are:
[0015] 1. In this utility model, the limiting component is designed to attach the limiting plate to the surface of the tail fin. By attaching multiple sets of limiting plates to the surface of the tail fin, the tail fin can be limited, which facilitates the operation of the tail fin. Furthermore, the rotational connection between the first rotating frame and the second rotating frame and the sliding connection between the limiting plate allow multiple sets of limiting plates to fit different models of tail fins, which facilitates the fixing of different models of tail fins. This saves materials for making different types of assembly tooling for different models of tail fins and improves the aircraft model development process.
[0016] 2. In this utility model, by designing a movable plate, the second telescopic cylinder is activated, which drives the connecting frame to move, causing the movable plate to move, which in turn drives the tail fin, which is fixed by multiple sets of limiting components, to move. This facilitates the adjustment of the tail fin's height and makes it easier for workers to assemble the tail fin with the aircraft. Attached Figure Description
[0017] Figure 1 This is a schematic diagram of the overall structure of this utility model;
[0018] Figure 2 It is the connecting shell structure schematic view of the utility model;
[0019] Figure 3 It is the limiting assembly structure schematic view of the utility model;
[0020] Figure 4 It is the sleeve internal structure schematic view of the utility model.
[0021] In the drawing: 1, rack main body; 2, moving plate; 3, connecting shell; 4, limiting assembly; 5, first rotating frame; 6, second rotating frame; 7, sleeve; 8, sliding rod; 9, limiting plate; 10, fixed plate; 11, first damping spring; 12, support block; 13, second damping spring; 14, friction block; 15, connecting frame. DETAILED DESCRIPTION
[0022] The technical scheme in the embodiments of the utility model will be described clearly and completely below in conjunction with the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the utility model.
[0023] Embodiment:
[0024] Please refer to Figures 1-4 The utility model provides a technical scheme:
[0025] An airplane vertical tail wing assembly tool includes a rack main body 1, the inside of the rack main body 1 is slidably connected with a moving plate 2, both ends of the top of the moving plate 2 are fixedly connected with a connecting shell 3, and the connecting shell 3 is provided with a limiting assembly 4 on both sides.
[0026] The limiting assembly 4 is used for limiting the tail wing, and is composed of a first rotating frame 5, a second rotating frame 6, a plurality of sleeves 7, a plurality of sliding rods 8 and a plurality of limiting plates 9. The first rotating frame 5 is located in the inside of the connecting shell 3, the second rotating frame 6 is located on the outside of the first rotating frame 5, the plurality of sleeves 7 are fixedly connected to the outside of the first rotating frame 5 and the second rotating frame 6 respectively, the sliding rod 8 is slidably connected to the inside of the sleeve 7, and the limiting plate 9 is fixedly connected to one end of the sliding rod 8 away from the sleeve 7.
[0027] Further, the inside of the connecting shell 3 is slidably connected with two groups of fixed plates 10, the first rotating frame 5 and the second rotating frame 6 are rotatably connected with the fixed plates 10, the two groups of fixed plates 10 are fixedly connected with each other, the first rotating frame 5 and the second rotating frame 6 are rotatably connected with the fixed plates 10, when the first rotating frame 5 and the second rotating frame 6 rotate, the fixed plates 10 can guide them to prevent the first rotating frame 5 and the second rotating frame 6 from deviating, and when the fixed plates 10 displace, the first rotating frame 5 and the second rotating frame 6 can be displaced.
[0028] Wherein, the end of the connecting shell 3 away from the moving plate 2 is fixedly connected with the first telescopic cylinder, the driving end of the first telescopic cylinder extends to the inside of the connecting shell 3 and is fixedly connected with the connection place of the two groups of fixed plates 10, starting the first telescopic cylinder can displace the two groups of fixed plates 10, the multiple groups of the first rotating frame 5 and the second rotating frame 6 can displace, displace the sleeve 7, displace the sliding rod 8, and displace the limiting plate 9 to contact with the empennage.
[0029] Secondly, the end of the first rotating frame 5 close to the fixed plate 10 is fixedly connected with the first damping spring 11, the end of the first rotating frame 5 close to the second rotating frame 6 is fixedly connected with the support block 12, the support block 12 is circular structure design, the inside of the sleeve 7 is fixedly connected with the second damping spring 13, when the limiting plate 9 contacts with the empennage, the sliding rod 8 is displaced by the relative force, displace the sleeve 7, make the first rotating frame 5 and the second rotating frame 6 rotate, the second rotating frame 6 contacts with the first rotating frame 5 through the support block 12, extrude the first damping spring 11, the first damping spring 11 generates rebound force by extrusion, make the first rotating frame 5 and the second rotating frame 6 present "V" type structure design, cooperate with the second damping spring 13 to displace the sliding rod 8, displace the limiting plate 9, make the limiting plate 9 adhere to the surface of the empennage, through multiple groups of the limiting plate 9 adhering to the surface of the empennage, can limit the empennage, facilitate to operate the empennage, and the rotatable connection of the first rotating frame 5 and the second rotating frame 6 and the sliding connection of the limiting plate 9 make multiple groups of the limiting plate 9 can adhere to different models of the empennage, facilitate to fix different models of the empennage, save the materials of making different kinds of assembly tooling for different models of the empennage, improve the aircraft model development process.
[0030] Further, the end of the limiting plate 9 away from the sliding rod 8 is fixedly connected with multiple groups of the friction block 14, the friction block 14 is semicircular structure design, multiple groups of the friction block 14 are equidistantly distributed outside the limiting plate 9, when the limiting plate 9 contacts with the empennage, through multiple groups of the friction block 14 can increase the friction force between the limiting plate 9 and the empennage, prevent the limiting plate 9 from slipping, affect the limitation of the empennage.
[0031] Further, the inside of the moving plate 2 is fixedly connected with a connecting frame 15, the bottom of the connecting frame 15 is fixedly connected with the driving end of a second telescopic cylinder around, the second telescopic cylinder is fixedly connected to the inside of the rack main body 1, the second telescopic cylinder is started, the connecting frame 15 is driven to displace, so that the moving plate 2 is displaced, a plurality of limiting assemblies 4 are driven to displace the tail wing fixedly limited, the height of the tail wing is adjusted, and the staff is facilitated to assemble the tail wing and the aircraft.
[0032] In the embodiment, the implementation scene is specifically: in actual use, the tail wing is placed on the top of the moving plate 2 and between the two groups of connecting shells 3, the first telescopic cylinder is started, the two groups of fixed plates 10 are driven to displace, a plurality of two groups of first rotating frames 5 and second rotating frames 6 can displace, the sleeve 7 is driven to displace, the sliding rod 8 is displaced, the limiting plate 9 is driven to displace, the limiting plate 9 is in contact with the tail wing, when the limiting plate 9 is in contact with the tail wing, the sliding rod 8 is displaced by the relative force, the sleeve 7 is displaced, the first rotating frame 5 and the second rotating frame 6 are rotated, the second rotating frame 6 is in contact with the first rotating frame 5 through the supporting block 12, the first damping spring 11 is extruded, the first damping spring 11 is extruded to generate a rebound force, the first rotating frame 5 and the second rotating frame 6 are designed in a “V” shape, the second damping spring 13 drives the sliding rod 8 to displace, the limiting plate 9 is displaced, the limiting plate 9 is attached to the surface of the tail wing, a plurality of limiting plates 9 are attached to the surface of the tail wing, so that the tail wing can be limited, the tail wing is conveniently operated, the rotating connection of the first rotating frame 5 and the second rotating frame 6 and the sliding connection of the limiting plate 9 make a plurality of limiting plates 9 be attached to tail wings of different models, different models of tail wings are conveniently fixed, materials for manufacturing different types of assembly fixtures for different models of tail wings are saved, the development process of aircraft models is improved, the second telescopic cylinder is started, the connecting frame 15 is displaced, the moving plate 2 is displaced, a plurality of limiting assemblies 4 are driven to displace the tail wing fixedly limited, the height of the tail wing is adjusted, and the staff is facilitated to assemble the tail wing and the aircraft.
[0033] Although the embodiments of the utility model have been shown and described, it can be understood by those skilled in the art that various changes, modifications, replacements and modifications can be made to these embodiments without departing from the principles and spirits of the utility model, the scope of the utility model is defined by the appended claims and their equivalents.
Claims
1. An aircraft vertical tail assembly fixture comprising a frame body (1), characterised in that: The inside of the rack body (1) is slidably connected with a moving plate (2), both ends of the top of the moving plate (2) are fixedly connected with a connecting shell (3), and both sides of the connecting shell (3) are provided with a limiting assembly (4). The limiting assembly (4) is used for limiting the tail wing, and is composed of a first rotating frame (5), a second rotating frame (6), a plurality of sleeves (7), a plurality of sliding rods (8) and a plurality of limiting plates (9). The first rotating frame (5) is located in the inside of the connecting shell (3), the second rotating frame (6) is located on the outside of the first rotating frame (5), a plurality of sleeves (7) are fixedly connected to the outside of the first rotating frame (5) and the second rotating frame (6), the sliding rod (8) is slidably connected to the inside of the sleeve (7), and the limiting plate (9) is fixedly connected to one end of the sliding rod (8) away from the sleeve (7).
2. An aircraft vertical tail assembly tooling fixture as defined in claim 1, wherein: The inside of the connecting shell (3) is slidably connected with two groups of fixed plates (10), the first rotating frame (5) and the second rotating frame (6) are rotatably connected with the fixed plates (10), and the two groups of fixed plates (10) are fixedly connected with each other.
3. An aircraft vertical tail assembly tooling fixture as defined in claim 2, wherein: One end of the connecting shell (3) away from the moving plate (2) is fixedly connected with a first telescopic air cylinder, and the driving end of the first telescopic air cylinder extends into the inside of the connecting shell (3) and is fixedly connected with the connecting position of the two groups of fixed plates (10).
4. An aircraft vertical tail assembly tooling fixture as defined in claim 2, wherein: One end of the first rotating frame (5) close to the fixed plate (10) is fixedly connected with a first damping spring (11), one end of the first rotating frame (5) close to the second rotating frame (6) is fixedly connected with a supporting block (12), and the supporting block (12) is designed in a circular structure.
5. An aircraft vertical tail assembly tooling fixture as defined in claim 1, wherein: The sliding rod (8) extending into the inside of the sleeve (7) is fixedly connected with a second damping spring (13), and one end of the second damping spring (13) away from the sliding rod (8) is fixedly connected with the sleeve (7).
6. An aircraft vertical tail assembly tooling fixture as defined in claim 1, wherein: One end of the limiting plate (9) away from the sliding rod (8) is fixedly connected with a plurality of friction blocks (14), the friction blocks (14) are designed in a semicircular structure, and a plurality of friction blocks (14) are distributed at equal intervals on the outside of the limiting plate (9).
7. An aircraft vertical tail assembly tooling fixture as defined in claim 1, wherein: The inside of the moving plate (2) is fixedly connected with a connecting frame (15), the driving end of a second telescopic air cylinder is fixedly connected to the bottom of the connecting frame (15), and the second telescopic air cylinder is fixedly connected to the inside of the rack body (1).