Special airplane bracket for aviation maintenance

Abstract

The utility model discloses a special airplane bracket for aviation maintenance, and belongs to the field of special airplane brackets. The special airplane bracket for aviation maintenance comprises a fixed base, a fixed block is arranged on the fixed base, a supporting column is arranged on the fixed block, a carrying plate is arranged at the end, away from the fixed block, of the supporting column, and the special airplane bracket further comprises a connecting rotary hinge which is arranged on the carrying plate. And a movable plate is arranged at the movable end of the connecting rotary hinge. The bracket solves the problems that when an existing bracket special for the airplane is used for carrying the airplane, the bottom of the airplane is round due to the fact that wind resistance is reduced, and the surface of a carrying plate of a traditional bracket special for the airplane is flat and cannot be attached to the bottom of the airplane in shape.

Description

Technical Field

[0001] This utility model relates to the field of aircraft-specific brackets, specifically an aircraft-specific bracket used for aircraft maintenance. Background Technology

[0002] Aviation maintenance refers to the maintenance and repair of aircraft and their technical equipment to ensure aircraft safety. Aviation maintenance is a prerequisite and necessary condition for the use of aircraft and an important part of the aviation industry.

[0003] Chinese Patent No. CN217230121U discloses a special aircraft support for aviation maintenance, comprising a main body, the main body including: a chassis, on which a mounting frame and guide components are mounted; a lifting component for lifting during aircraft maintenance, the lifting component being mounted on the mounting frame; and an auxiliary component for facilitating the movement of the aircraft to a designated height by the user during maintenance, the auxiliary component being mounted on the guide components. By incorporating the auxiliary component, during use, a drive motor can be used to move the operating platform up and down, transporting the user to a suitable work position. This eliminates the need for a steel frame structure erected on the outside of the aircraft to raise the user's position for maintenance and inspection, solving the problems of slow construction speed and time-consuming and labor-intensive steel frame structures, and effectively improving the efficiency of aircraft maintenance and inspection by the user.

[0004] When the aircraft-specific bracket of the aforementioned patent is used to support an aircraft, the aircraft has a round bottom shape to reduce wind resistance. In contrast, the surface of the traditional aircraft-specific bracket is relatively flat and cannot fit the shape of the aircraft bottom. Utility Model Content

[0005] The purpose of this utility model is to provide a special aircraft bracket for aviation maintenance. It features a rotating hinge at one end of the support plate, with a movable plate on the movable end of the hinge. A support column is located at the lower end of the support plate, with a limit plate on its outer surface. The limit plate is positioned below the movable plate. When an aircraft is placed on the upper part of the support plate, the movable plate bends due to the aircraft's weight, causing the aircraft to fall between the two movable plates. To prevent the aircraft from falling due to excessive bending angle, the lower end of the movable plate abuts against the limit plate when it bends to a certain angle, thus stopping the movable plate from bending further. This solves the problems mentioned in the background art.

[0006] To achieve the above objectives, this utility model provides the following technical solution: a special aircraft bracket for aviation maintenance, comprising a fixed base, a fixed block on the fixed base, a support column on the fixed block, a support plate on the end of the support column away from the fixed block, and a connecting rotating hinge disposed on the support plate. A movable plate is disposed on the movable end of the connecting rotating hinge. A limit plate is disposed on the support column. A connecting rod is disposed on the fixed base, a second hydraulic cylinder is disposed on the connecting rod, and a lifting plate is disposed on the movable end of the second hydraulic cylinder.

[0007] Preferably, a first hydraulic cylinder is provided at the lower end of the fixed base, and the fixed end of the first hydraulic cylinder is bolted to the fixed base.

[0008] Preferably, a ground contact base is provided on the movable end of the first hydraulic cylinder, and the ground contact base is welded to the first hydraulic cylinder.

[0009] Preferably, the lower end of the fixed base is provided with a caster wheel, and the caster wheel is bolted to the fixed base.

[0010] Preferably, the outer surface of the support plate is provided with a first anti-slip pad.

[0011] Preferably, the movable plate is provided with a second anti-slip pad.

[0012] Compared with the prior art, the beneficial effects of this utility model are as follows:

[0013] This utility model features a rotating hinge at one end of a support plate, with a movable plate on the movable end of the hinge. A support column is located at the lower end of the support plate, and a limiting plate is provided on the outer surface of the support column. The limiting plate is located below the movable plate. When an aircraft is placed on the upper part of the support plate, the movable plate bends due to the weight of the aircraft, causing the aircraft to fall between the two movable plates. To prevent the aircraft from falling due to a large bending angle, the lower end of the movable plate abuts against the limiting plate when the movable plate bends to a certain angle, preventing the movable plate from bending further. This effectively avoids the problem that existing aircraft-specific support plates cannot conform to the shape of the aircraft's bottom when carrying aircraft, as the aircraft's bottom shape is rounded to reduce wind resistance. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the overall external structure of this utility model;

[0015] Figure 2 This is a top view of the overall structure of this utility model;

[0016] Figure 3 This is a schematic diagram of the overall main structure of this utility model.

[0017] In the diagram: 1. Fixed base; 2. First hydraulic cylinder; 3. Ground contact base; 4. Caster wheel; 5. Fixed block; 6. Support column; 7. Loading plate; 8. Connecting rotating hinge; 9. Movable plate; 10. Limiting plate; 11. First anti-slip pad; 12. Second anti-slip pad; 13. Second hydraulic cylinder; 14. Lifting plate; 15. Connecting rod. Detailed Implementation

[0018] 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.

[0019] To address the problem that in existing technologies where aircraft-specific carriers support aircraft, the aircraft's underside is circular to reduce wind resistance, while the surface of traditional aircraft-specific carrier plates is relatively flat and cannot conform to the aircraft's underside shape, this embodiment provides the following technical solution:

[0020] An aircraft-specific bracket for aviation maintenance includes a fixed base 1, a fixed block 5 on the fixed base 1, a support column 6 on the fixed block 5, a support plate 7 on the end of the support column 6 away from the fixed block 5, a connecting rotating hinge 8 on the support plate 7, a movable plate 9 on the movable end of the connecting rotating hinge 8, a limit plate 10 on the support column 6, a connecting rod 15 on the fixed base 1, a second hydraulic cylinder 13 on the connecting rod 15, a lifting plate 14 on the movable end of the second hydraulic cylinder 13, a first hydraulic cylinder 2 at the lower end of the fixed base 1, the fixed end of the first hydraulic cylinder 2 being bolted to the fixed base 1, a ground contact base 3 on the movable end of the first hydraulic cylinder 2 being welded to the first hydraulic cylinder 2, a caster wheel 4 at the lower end of the fixed base 1 being bolted to the fixed base 1, a first anti-slip pad 11 on the outer surface of the support plate 7, and a second anti-slip pad 12 on the movable plate 9.

[0021] In this embodiment, please refer to Figures 1-3A rotating hinge 8 is provided at one end of the support plate 7. A movable plate 9 is provided on the movable end of the rotating hinge 8. A support column 6 is provided at the lower end of the support plate 7. A limit plate 10 is provided on the outer surface of the support column 6. The limit plate 10 is located below the movable plate 9. When the aircraft is placed on the upper end of the support plate 7, the movable plate 9 bends due to the weight of the aircraft, causing the aircraft to fall between the two movable plates 9. In order to prevent the aircraft from falling due to a large bending angle of the movable plate 9, when the movable plate 9 bends to a certain angle, the lower end of the movable plate 9 abuts against the limit plate 10 to stop the movable plate 9 from bending further.

[0022] Working principle: The operator first uses the casters 4 to move the fixed base 1 to the lower end of the aircraft. Then, the movable end of the first hydraulic cylinder 2 lifts the casters 4 off the ground to prevent the fixed base 1 from sliding. Then, the second hydraulic cylinder 13 drives the lifting plate 14 to rise, slightly lifting the aircraft to a small height. A rotating connecting hinge 8 is provided at one end of the support plate 7. A movable plate 9 is provided on the movable end of the rotating connecting hinge 8. A support column 6 is provided at the lower end of the support plate 7. A limit plate 10 is provided on the outer surface of the support column 6. The limit plate 10 is located below the movable plate 9. When the aircraft is placed on the upper end of the support plate 7, the movable plate 9 bends due to the weight of the aircraft, causing the aircraft to fall between the two movable plates 9. In order to prevent the aircraft from falling due to a large bending angle of the movable plate 9, when the movable plate 9 bends to a certain angle, the lower end of the movable plate 9 abuts against the limit plate 10 to stop the movable plate 9 from bending further.

[0023] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0024] 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-specific bracket for aircraft maintenance, comprising a fixed base (1), a fixed block (5) provided on the fixed base (1), a support column (6) provided on the fixed block (5), and a support plate (7) provided on the end of the support column (6) away from the fixed block (5). Its features are: It also includes a connecting rotating hinge (8), which is mounted on the support plate (7). A movable plate (9) is provided on the movable end of the connecting rotating hinge (8). A limit plate (10) is provided on the support column (6). A connecting rod (15) is provided on the fixed base (1). A second hydraulic cylinder (13) is provided on the connecting rod (15). A lifting plate (14) is provided on the movable end of the second hydraulic cylinder (13).

2. The aircraft-specific bracket for aircraft maintenance according to claim 1, characterized in that: The lower end of the fixed base (1) is provided with a first hydraulic cylinder (2), and the fixed end of the first hydraulic cylinder (2) is bolted to the fixed base (1).

3. The aircraft-specific bracket for aircraft maintenance according to claim 2, characterized in that: The first hydraulic cylinder (2) is provided with a ground contact base (3) on its movable end, and the ground contact base (3) is welded to the first hydraulic cylinder (2).

4. The aircraft-specific bracket for aircraft maintenance according to claim 1, characterized in that: The fixed base (1) is provided with a caster wheel (4) at its lower end, and the caster wheel (4) is bolted to the fixed base (1).

5. The aircraft-specific bracket for aircraft maintenance according to claim 1, characterized in that: The outer surface of the support plate (7) is provided with a first anti-slip pad (11).

6. The aircraft-specific bracket for aircraft maintenance according to claim 1, characterized in that: A second anti-slip pad (12) is provided on the movable plate (9).

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