Aircraft internal line maintenance protective cover

Abstract

The utility model discloses an aircraft internal line maintenance protective cover, which comprises a central control cabin and a protective cover, four corners of the top of the central control cabin are respectively provided with a first mounting plate, the top of each first mounting plate is fixedly connected with a stand column, the top of each stand column is fixedly connected with a sliding rod, and the top of each sliding rod is fixedly connected with a conical top head. When lines inside an airplane are overhauled, only the protective cover needs to be pressed to enable the buckle to slide towards the lower portion of the conical top head, the buckle has an elastic effect due to connection of the movable rod and the spring, then the buckle slides to the lower portion of the conical bottom head, and then the buckle is lifted outwards through a hand buckle groove formed in the protective cover. The conical bottom head is attached to the conical top head under the lifting of the buckle to form a conical structure, then the buckle enables the attached bevel edge to slide outwards, at the moment, the protective cover can be rapidly disassembled to overhaul the internal circuit of the airplane, and on the contrary, the effect of rapid installation can be achieved to replace inconvenience caused by bolt disassembly and assembly.

Description

Technical Field

[0001] The utility model belongs to the technical field of protective covers, and particularly relates to a protective cover for aircraft internal line maintenance. Background Technique

[0002] The protective cover for aircraft internal line maintenance is a safety device used to protect workers and aircraft structures from damage during the maintenance and repair of aircraft internal lines, and at the same time prevent tools and components from accidentally damaging the lines. This protective cover is usually designed to be detachable to facilitate line inspection and repair by maintenance personnel. It should possess key characteristics such as safety protection, easy disassembly and assembly, durability, light weight, user-friendly interface, compatibility, and aesthetics.

[0003] After the lines of the aircraft internal central control console are connected, they need to be protected by a protective cover. However, the protective cover is generally installed and connected to the central control console through bolts. When line maintenance is required, the bolts need to be repeatedly disassembled and assembled. After multiple disassembly and assembly operations, there is a possibility of thread slipping, which will bring certain inconvenience. Summary of the Utility Model

[0004] The technical problem to be solved by the utility model is to overcome the existing defects and provide a protective cover for aircraft internal line maintenance, so as to solve the problem that after the lines of the aircraft internal central control console are connected, they need to be protected by a protective cover. However, the protective cover is generally installed and connected to the central control console through bolts. When line maintenance is required, the bolts need to be repeatedly disassembled and assembled. After multiple disassembly and assembly operations, there is a possibility of thread slipping, which will bring certain inconvenience as mentioned in the above background technique.

[0005] To achieve the above purpose, the utility model provides the following technical solution: A protective cover for aircraft internal line maintenance, including a central control bin and a protective cover. At the four corners of the top of the central control bin, first mounting plates are provided. A column is fixedly connected to the top of the first mounting plate. A sliding rod is fixedly connected to the top of the column. A conical top head is fixedly connected to the top of the sliding rod. A conical bottom head is slidably connected to the outside of the sliding rod. On one side of the top of the central control bin, elastic telescopic rods are symmetrically and fixedly connected. A support plate is fixedly connected to the top of the elastic telescopic rod. At the four corners of the bottom of the protective cover, second mounting plates are provided. A locking cylinder is fixedly connected to the bottom of the second mounting plate. Sliding grooves are symmetrically arranged inside the locking cylinder. A moving rod is slidably connected inside the sliding groove. A buckle is fixedly connected to one end of the moving rod. A spring is arranged on the outside of the moving rod.

[0006] Preferably, an inclined groove is opened at the top of the column. The first mounting plate and the column are fixedly connected to the central control bin through bolts.

[0007] Preferably, the support plate is attached to the surface of the protective cover.

[0008] Preferably, a hand-holding groove is formed on one side of the protective cover.

[0009] Preferably, the second mounting plate and the locking cylinder are fixedly connected to the protective cover by bolts.

[0010] Preferably, the spring is fixedly connected between the sliding groove and the buckle.

[0011] Preferably, a limiting nut is threadedly connected to one end of the outer side of the moving rod.

[0012] Preferably, a wiring board is fixedly connected to the top of the central control bin, and wiring grooves are formed on the top of the wiring board.

[0013] Compared with the prior art, the present utility model provides a protective cover for overhauling internal lines of an aircraft, and has the following beneficial effects:

[0014] 1. By setting a protective cover for overhauling internal lines of an aircraft, when in use, the locking mechanism composed of the first mounting plate, the column, the inclined groove, the sliding rod, the conical top head and the conical bottom head is installed inside the central control bin, and the buckle mechanism composed of the second mounting plate, the locking cylinder, the sliding groove, the moving rod, the spring and the buckle is installed at the bottom of the protective cover. Then, when overhauling the internal lines of the aircraft, only need to press the protective cover to slide the buckle below the conical top head. Due to the connection of the moving rod and the spring, the buckle has an elastic effect, so that the buckle slides below the conical bottom head. Then, it can be lifted outwards through the hand-holding groove provided on the protective cover, so that the conical bottom head fits with the conical top head under the lifting of the buckle to form a conical structure. Then, the buckle slides outwards along the fitting hypotenuse. At this time, the protective cover can be quickly disassembled to overhaul the internal lines of the aircraft. On the contrary, a quick installation effect can be achieved to replace the inconvenience brought by bolt disassembly and assembly;

[0015] 2. By setting the wiring board and the wiring grooves, the wiring board and the wiring grooves provided on the top of the central control bin can distinguish and clamp the internal lines of the aircraft, which can facilitate the maintenance personnel to quickly overhaul, and at the same time can also keep the internal lines tidy.

[0016] Parts not involved in the device are the same as or can be implemented by the prior art. The structure of the present utility model is scientific and reasonable, safe and convenient to use, and provides great help for people. Description of the Drawings

[0017] The drawings are used to provide further understanding of the present utility model, and constitute a part of the specification. Together with the embodiments of the present utility model, they are used to explain the present utility model, and do not constitute a limitation to the present utility model. In the drawings:

[0018] Figure 1Schematic axonometric structure diagram of one side of a protective cover for aircraft internal circuit maintenance proposed by the present utility model;

[0019] Figure 2 Schematic structure diagram of a circuit support plate of a protective cover for aircraft internal circuit maintenance proposed by the present utility model;

[0020] Figure 3 Schematic structure diagram of a column of a protective cover for aircraft internal circuit maintenance proposed by the present utility model;

[0021] Figure 4 Schematic structure diagram of a sliding rod of a protective cover for aircraft internal circuit maintenance proposed by the present utility model;

[0022] Figure 5 Schematic structure diagram of a buckle of a protective cover for aircraft internal circuit maintenance proposed by the present utility model;

[0023] Figure 6 Schematic cross-sectional structure diagram of a protective cover for aircraft internal circuit maintenance proposed by the present utility model;

[0024] In the figure: central control bin 1, first mounting plate 2, column 3, inclined groove 4, sliding rod 5, conical top head 6, conical bottom head 7, elastic telescopic rod 8, support plate 9, protective cover 10, hand buckle groove 11, second mounting plate 12, locking cylinder 13, sliding groove 14, moving rod 15, spring 16, buckle 17, limit nut 18, wiring board 19, wiring groove 20. Specific embodiments

[0025] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0026] Please refer to Figures 1-6, the present utility model provides a technical solution: an aircraft internal line maintenance protective cover, including a central control compartment 1 and a protective cover 10. At the four corners of the top of the central control compartment 1, there are first mounting plates 2. On the top of the first mounting plates 2, there are fixed columns 3. On the top of the columns 3, there are fixed sliding rods 5. On the top of the sliding rods 5, there are fixed conical heads 6. The outside of the sliding rods 5 is slidably connected with conical bottoms 7. On one side of the top of the central control compartment 1, there are symmetrically fixed elastic telescopic rods 8. On the top of the elastic telescopic rods 8, there is a fixed support plate 9. At the four corners of the bottom of the protective cover 10, there are second mounting plates 12. At the bottom of the second mounting plates 12, there are fixed locking cylinders 13. Inside the locking cylinders 13, there are symmetrically arranged chutes 14. Inside the chutes 14, there are slidably connected moving rods 15. One end of the moving rods 15 is fixedly connected with a buckle 17. On the outside of the moving rods 15, there is a spring 16. Install the locking mechanism composed of the first mounting plate 2, the column 3, the inclined slot 4, the sliding rod 5, the conical head 6 and the conical bottom 7 inside the central control compartment 1. Install the buckle mechanism composed of the second mounting plate 12, the locking cylinder 13, the chute 14, the moving rod 15, the spring 16 and the buckle 17 at the bottom of the protective cover 10. Then, when maintaining the aircraft internal lines, only need to press the protective cover 10 to slide the buckle 17 below the conical head 6. Due to the connection of the moving rod 15 and the spring 16, the buckle 17 has an elastic effect. Then the buckle 17 slides below the conical bottom 7. Then it can be lifted outwards through the hand-held slot 11 provided on the protective cover 10, so that the conical bottom 7 fits with the conical head 6 under the lifting of the buckle 17 to form a conical structure. Then the buckle 17 slides outwards along the fitting hypotenuse. At this time, the protective cover can be quickly disassembled to maintain the aircraft internal lines. On the contrary, a quick installation effect can be achieved.

[0027] In the present utility model, preferably, an inclined slot 4 is opened at the top of the column 3, and the first mounting plate 2 and the column 3 are fixedly connected to the central control compartment 1 by bolts.

[0028] In the present utility model, preferably, the support plate 9 is attached to the surface of the protective cover 10.

[0029] In the present utility model, preferably, a hand-held slot 11 is opened on one side of the protective cover 10.

[0030] In the present utility model, preferably, the second mounting plate 12 and the locking cylinder 13 are fixedly connected to the protective cover 10 by bolts.

[0031] In the present utility model, preferably, the spring 16 is fixedly connected between the chute 14 and the buckle 17.

[0032] In the present utility model, preferably, a limiting nut 18 is threadedly connected to one end of the outside of the moving rod 15.

[0033] In the present utility model, preferably, a wiring board 19 is fixedly connected to the top of the central control bin 1, and wiring grooves 20 are formed in the top of the wiring board 19.

[0034] The working principle and usage process of the present utility model: During use, a structure including a central control bin and a protective cover is combined together. At the four corners of the top of the central control bin, there are first mounting plates, on which columns are fixedly connected. The top of the columns is fixedly connected with sliding rods, and the top of the sliding rods is fixedly connected with conical heads. The outer side of the sliding rods is slidably connected with conical bottom heads. On one side of the top of the central control bin, elastic telescopic rods are symmetrically and fixedly connected, and their tops are fixedly connected with a support plate. At the four corners of the bottom of the protective cover, there are second mounting plates, and locking cylinders are fixedly connected to their bottoms. Inside the locking cylinders, chutes are symmetrically arranged, and moving rods are slidably connected inside the chutes. One end of the moving rod is fixedly connected with a buckle, and a spring is arranged on its outer side. Then, when repairing the internal lines of the aircraft, the operator only needs to press the protective cover to slide the buckle below the conical head. Due to the elastic effect of the connection between the moving rod and the spring, the buckle will slide below the conical bottom head. Then, the operator can lift it outwards through the hand-holding groove provided on the protective cover, so that the conical bottom head fits with the conical head to form a conical structure. At this time, the buckle will slide outwards along the fitting hypotenuse, and the operator can quickly disassemble the protective cover to repair the internal lines of the aircraft. On the contrary, by pressing the protective cover and pushing the buckle towards the conical head direction, the conical bottom head can be separated from the conical head, achieving the effect of quickly installing the protective cover. In addition, inclined grooves are formed at the top of the columns, and the first mounting plates and the columns are fixedly connected to the central control bin through bolts, enhancing the structural stability. The support plate fits on the surface of the protective cover, enabling the protective cover to better maintain its shape. A hand-holding groove is formed on one side of the protective cover, facilitating the operator's lifting operation. The second mounting plates and the locking cylinders are fixedly connected to the protective cover through bolts, ensuring the stability of the buckle mechanism. The spring is fixedly connected between the chute and the buckle, providing an elastic force. A limiting nut is threadedly connected to the outer end of the moving rod, restricting the sliding range of the moving rod. A wiring board is fixedly connected to the top of the central control bin, and wiring grooves are formed in the top of the wiring board, facilitating the layout of the lines. Through the above working principle, the protective cover for repairing the internal lines of the aircraft can achieve quick disassembly and installation, facilitating the repair work of the internal lines of the aircraft and improving work efficiency and safety.

[0035] Although the embodiments of the present utility model have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present utility model. The scope of the present utility model is defined by the appended claims and their equivalents.

Claims

1. An aircraft internal circuit maintenance protective cover, comprising a central control compartment (1) and a protective cover (10), characterized in that: At the four corners of the top of the central control bin (1), first mounting plates (2) are provided. A column (3) is fixedly connected to the top of the first mounting plate (2). A sliding rod (5) is fixedly connected to the top of the column (3). A conical top head (6) is fixedly connected to the top of the sliding rod (5). A conical bottom head (7) is slidably connected to the outer side of the sliding rod (5). Elastic telescopic rods (8) are symmetrically and fixedly connected to one side of the top of the central control bin (1). A support plate (9) is fixedly connected to the top of the elastic telescopic rod (8). At the four corners of the bottom of the protective cover (10), second mounting plates (12) are provided. A locking cylinder (13) is fixedly connected to the bottom of the second mounting plate (12). Chute grooves (14) are symmetrically arranged inside the locking cylinder (13). A moving rod (15) is slidably connected inside the chute groove (14). A buckle (17) is fixedly connected to one end of the moving rod (15). A spring (16) is arranged on the outer side of the moving rod (15).

2. The protective cover for aircraft internal circuit maintenance according to claim 1, characterized in that: An inclined groove (4) is formed at the top of the column (3). The first mounting plate (2) and the column (3) are fixedly connected to the central control bin (1) by bolts.

3. The protective cover for aircraft internal circuit maintenance according to claim 1, characterized in that: The support plate (9) is attached to the surface of the protective cover (10).

4. The aircraft internal circuit maintenance protective cover according to claim 1, wherein: A hand-holding groove (11) is formed on one side of the protective cover (10).

5. The aircraft internal circuit maintenance protective cover according to claim 1, wherein: The second mounting plate (12) and the locking cylinder (13) are fixedly connected to the protective cover (10) by bolts.

6. The aircraft internal circuit maintenance protective cover according to claim 1, wherein: The spring (16) is fixedly connected between the chute groove (14) and the buckle (17).

7. The protective cover for aircraft internal circuit maintenance according to claim 1, characterized in that: A limit nut (18) is threadedly connected to one end of the outer side of the moving rod (15).

8. The protective cover for aircraft internal circuit maintenance according to claim 1, wherein: A wiring board (19) is fixedly connected to the top of the central control bin (1). Wiring grooves (20) are formed at the top of the wiring board (19).

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