Airplane identification structure with three-proofing and noctilucent functions

Abstract

The utility model discloses an airplane identification structure with three-proofing and noctilucent functions, which relates to the technical field of airplane identification and comprises a protective shell with a mounting opening in the top. The number of the lamp strips is multiple, and the multiple lamp strips are fixedly connected into the protective shell; the mounting mechanism is arranged in the protective shell, the mounting mechanism comprises a limiting part and two clamping piece plates, the limiting part is arranged in the protective shell, and the two clamping piece plates are movably inserted into the protective shell. According to the aircraft identification structure with the three-proofing and noctilucent functions, through the use of a lamp belt, an internal identification can be illuminated, it is guaranteed that observation can be conducted during night driving, the overall effect in the using process is improved, through the use of a communicating hole, the interior and the exterior of the device can be communicated, and the overall effect is improved. Influence on overall use due to water vapor generated by different internal and external temperatures is avoided, and the water heater is simple in structure and can bear the test of severe environments.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft marking, in particular to an aircraft marking structure with three-proof and luminous functions. Background Art

[0002] Aircraft exterior markings are an essential component of aircraft exterior painting. They are used to provide staff with relevant operational notifications, prompts, instructions and warnings during the normal use and maintenance of the aircraft (normal flight, ground service, regular inspection and maintenance, etc.), and are used to improve the maintainability and safety of the aircraft during operation. When a civil airliner is cruising, its speed relative to the earth's surface is about 900km / h, and there will be intense friction between the air and the aircraft surface.

[0003] The authorization publication number "CN218768548U" records "an adhesive label for aircraft surface, comprising a label main body and a release layer adhered to the upper and lower surfaces of the label main body, which can play an effective protective role during the storage period before the construction of the label main body. The label main body is composed of an adhesive layer, a substrate layer, a label layer, a conductive layer, a corrosion-resistant layer and a wear-resistant layer. The upper and lower surfaces of the substrate layer are both provided with an adhesive layer, the label layer is adhered to the lower surface of the adhesive layer below, the conductive layer is coated on the lower surface of the label layer, the corrosion-resistant layer is coated on the lower surface of the conductive layer, and the wear-resistant layer is coated on the lower surface of the corrosion-resistant layer; the adhesive label for aircraft surface proposed by the utility model has the advantages of simple structure, convenient pasting, convenient maintenance, no damage to the paint surface, and can ensure clear text or patterns; at the same time, it has excellent adhesion, conductivity, corrosion resistance, and wear resistance. The label can withstand the test of harsh environment after layers of protection."

[0004] The above patent has the advantages of simple structure, convenient pasting, easy maintenance, no damage to the paint surface, and can ensure the clarity of text or patterns; at the same time, it has excellent adhesion, conductivity, corrosion resistance, and wear resistance. The logo can withstand the test of harsh environment after layers of protection. However, during use, it cannot remind at night, affecting the use effect. Utility Model Content

[0005] The utility model provides an aircraft identification structure with three-proof and luminous functions. By using a light strip, the internal identification can be illuminated to ensure that it can be observed when driving at night, thereby improving the overall effect during use. By using a connecting hole, the inside and outside of the device can be connected to avoid different temperatures inside and outside, thereby avoiding the generation of water vapor and affecting the overall use. In addition, the structure is simple and can withstand the test of harsh environments.

[0006] To achieve the above objectives, the utility model is implemented through the following technical solutions: an aircraft identification structure with three-proof and luminous functions, including:

[0007] A protective shell with a mounting opening on the top;

[0008] A plurality of light strips are provided, and the plurality of light strips are fixedly connected in the protective shell;

[0009] A mounting mechanism is disposed in the protective shell, the mounting mechanism comprising a limiting component and two clip plates, the limiting component is disposed in the protective shell, the two clip plates are movably inserted in the protective shell, and the two clip plates are connected to the limiting component; and

[0010] A communication hole is provided on one side of the outer surface of the protective shell.

[0011] Furthermore, the limiting component includes:

[0012] A load-bearing assembly is disposed in the protective shell and is used to bear the clip plate; and

[0013] The positioning component is arranged on the protective shell and is used for positioning the position of the clip plate.

[0014] Furthermore, the bearing assembly is a limit frame, and the limit frame is fixedly connected in the protective shell.

[0015] Furthermore, the positioning assembly includes two snap-in strips and two snap-in grooves, each of the snap-in grooves is opened at the top of one side of the outer surface of each clip plate, the two snap-in strips are respectively fixedly connected to the two sides of the inner wall of the mounting port, and each snap-in strip is snap-connected to each snap-in groove.

[0016] Furthermore, a refractive protective film is fixedly connected to one side of the protective shell.

[0017] Furthermore, a fluorescent identification plate is installed between the two clip plates.

[0018] The utility model provides an aircraft identification structure with three-proof and luminous functions. It has the following beneficial effects:

[0019] (1) The aircraft identification structure with three-proof and luminous functions can illuminate the internal identification through the use of light strips, ensuring that it can be observed when driving at night, thereby improving the overall effect during use.

[0020] (2) The aircraft identification structure with three-proof and luminous functions can connect the inside and outside of the device through the use of connecting holes, avoiding the difference in temperature between the inside and outside, thereby preventing the generation of water vapor and affecting the overall use. In addition, the structure is simple and can withstand the test of harsh environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1This is a cross-sectional exploded view of the utility model from a first perspective;

[0022] Figure 2 It is a cross-sectional exploded view from a second viewing angle of the present utility model;

[0023] Figure 3 It is a partial cross-sectional view of the utility model;

[0024] Figure 4 This is a first-perspective stereogram of the present invention;

[0025] Figure 5 This is a stereoscopic diagram from a second viewing angle of the present invention.

[0026] In the figure: 1. Protective shell; 2. Snap-in strip; 3. Refractive protective film; 4. Snap-in groove; 5. Clip plate; 6. Fluorescent identification plate; 7. Limit frame; 8. Light strip; 9. Connecting hole; 10. Installation port. DETAILED DESCRIPTION

[0027] The following will clearly and completely describe the technical solutions in the embodiments of the utility model in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of them. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0028] See also Figure 1-5 The utility model provides a technical solution: an aircraft identification structure with three-proof and luminous functions, including:

[0029] A protective shell 1 with a mounting opening 10 on the top;

[0030] A plurality of light strips 8 are provided, and the plurality of light strips 8 are fixedly connected to the protective shell 1;

[0031] An installation mechanism is arranged in the protective shell 1, and the installation mechanism includes a limiting component and two clip plates 5. The limiting component is arranged in the protective shell 1, and the two clip plates 5 are both movably inserted in the protective shell 1, and the two clip plates 5 are both connected to the limiting component; and

[0032] The communicating hole 9 is opened on one side of the outer surface of the protective shell 1 .

[0033] In this embodiment: the installation port 10 facilitates the installation of the clip plate 5 inside the protective shell 1. The protective shell 1 has the functions of protecting the interior, being waterproof, dustproof and filtering ultraviolet rays to prevent the logo from fading. The light strip 8 provides fill light to the interior. One side of the connecting hole 9 on the protective shell 1 is made of opaque material, and the other side is made of transparent material to ensure the use effect. The clip plate 5 facilitates the fixed use of the logo, and the connecting hole 9 is connected to the outside to avoid different temperatures inside and outside, thereby generating water vapor and affecting the overall use.

[0034] Specifically, the limiting components include:

[0035] A bearing assembly, disposed in the protective shell 1, for bearing the clip plate 5; and

[0036] The positioning assembly is disposed on the protective shell 1 and is used to position the clip plate 5 .

[0037] In this embodiment: the bearing assembly facilitates the installation of the clip plate 5, and is connected and positioned for use through the positioning assembly.

[0038] Specifically, the bearing component is a limit frame 7 , and the limit frame 7 is fixedly connected in the protective shell 1 .

[0039] In this embodiment, the width of the limit frame 7 corresponds to the width of the two clip plates 5, so that the two clip plates 5 can be used.

[0040] Specifically, the positioning assembly includes two snap-in strips 2 and two snap-in grooves 4. Each snap-in groove 4 is opened at the top of one side of the outer surface of each clip plate 5. The two snap-in strips 2 are respectively fixedly connected to the two sides of the inner wall of the mounting port 10, and each snap-in strip 2 is snap-connected to each snap-in groove 4.

[0041] In this embodiment, the two clamping strips 2 and the two clamping grooves 4 are connected one by one to ensure the use effect.

[0042] Specifically, a refractive protective film 3 is fixedly connected to one side of the protective shell 1 .

[0043] In this embodiment: the refractive protective film 3 can refract the light to complete the use.

[0044] Specifically, a fluorescent identification plate 6 is installed between the two clip plates 5 .

[0045] In this embodiment, the fluorescent identification plate 6 absorbs the light of the light strip 8, and when the light strip 8 cannot be used, it can emit light by itself and complete the use.

[0046] When in use, the protective shell 1 is installed on the aircraft, and the required logo is selected, and the logo is placed between the two clip plates 5. After the two clip plates 5 are merged, they are inserted into the installation port 10, so that each clamping strip 2 is docked with each clamping groove 4, and the two clip plates 5 are fixed in the protective shell 1 to complete the use. During use, the light strip 8 is used for fill light, and the fluorescent logo plate 6 absorbs the light of the light strip 8. When the light strip 8 cannot be used, it can emit light by itself to complete the use. In addition, during use, it is connected with the outside through the connecting hole 9 to avoid different temperatures inside and outside, thereby avoiding the generation of water vapor and affecting the overall use.

[0047] The control method of the present invention is to control by manually starting and closing the switch. The wiring diagram of the power element and the provision of power supply are common knowledge in the field, and the present invention is mainly used to protect mechanical devices, so the present invention will not explain the control method and wiring arrangement in detail.

[0048] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can make equivalent replacements or changes within the technical scope disclosed by the present invention according to the technical scheme and the utility model concept of the present invention, which should be covered by the protection scope of the present invention.

Claims

1. An aircraft identification structure with three-proof and luminous functions, characterized in that: include: A protective shell (1) having a mounting opening (10) at the top; A plurality of light strips (8) are provided, and the plurality of light strips (8) are all fixedly connected in the protective shell (1); A mounting mechanism is arranged in the protective shell (1), the mounting mechanism comprising a limiting component and two clip plates (5), the limiting component is arranged in the protective shell (1), the two clip plates (5) are both movably inserted in the protective shell (1), and the two clip plates (5) are both connected to the limiting component; and A communication hole (9), wherein the communication hole (9) is opened on one side of the outer surface of the protective shell (1).

2. The aircraft identification structure with three-proof and luminous functions according to claim 1, characterized in that: The limiting component comprises: A bearing assembly is disposed in the protective shell (1) and is used to bear the clip plate (5); and The positioning component is arranged on the protective shell (1) and is used to position the clip plate (5).

3. The aircraft identification structure with three-proof and luminous functions according to claim 2, characterized in that: The bearing component is a limit frame (7), and the limit frame (7) is fixedly connected inside the protective shell (1).

4. The aircraft identification structure with three-proof and luminous functions according to claim 3, characterized in that: The positioning assembly comprises two snap-in strips (2) and two snap-in grooves (4), each of the snap-in grooves (4) being arranged at the top of one side of the outer surface of each clip plate (5), the two snap-in strips (2) being respectively fixedly connected to the two sides of the inner wall of the installation opening (10), and each snap-in strip (2) being snap-connected to each snap-in groove (4).

5. The aircraft identification structure with three-proof and luminous functions according to claim 4, characterized in that: A refractive protective film (3) is fixedly connected to one side of the protective shell (1).

6. The aircraft identification structure with three-proof and luminous functions according to claim 5, characterized in that: A fluorescent identification plate (6) is installed between the two clamping plates (5).

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