CN219612099U

CN219612099U - Antistatic structure for aircraft glass

Info

Publication number: CN219612099U
Application number: CN202320385843.2U
Authority: CN
Inventors: 吴倩颖; 曹玉彬; 陈文浩; 徐世勇; 庞浩然; 徐鹏; 孙伟; 谢竹青; 丁洋
Original assignee: Jiangsu Iron Anchor Technology Co ltd
Current assignee: Jiangsu Iron Anchor Technology Co ltd
Priority date: 2023-03-03
Filing date: 2023-03-03
Publication date: 2023-08-29
Anticipated expiration: 2033-03-03

Abstract

The utility model discloses an aircraft glass antistatic structure, which comprises: the aircraft glass body is arranged as electric heating glass and is provided with outer layer glass, inner layer glass and an electric heating module; the transparent conductive film layer is plated on the outer surface of the outer glass layer; a Z-shaped metal pressing plate; an elastic conductor adhered to the outer surface of the electric heating module; the metal net is connected with the Z-shaped metal pressing plate and the elastic conductor; the edge of the aircraft glass body is covered by sealant, the sealant covers the Z-shaped metal pressing plate, the metal net and the filler, and the lower end of the elastic conductor is exposed. According to the utility model, the transparent conductive film layer, the Z-shaped metal pressing plate, the metal net and the elastic conductor are used for conducting with the airframe, so that the grounding of the Z-shaped metal pressing plate is realized, the discharge phenomenon between the edge part of the Z-shaped metal pressing plate and the airframe window frame is avoided, and the probability of failure of the transparent part of the aircraft cockpit due to the electrostatic action in the flight process can be reduced.

Description

Antistatic structure for aircraft glass

Technical Field

The utility model belongs to the technical field of aircraft glass antistatic, and particularly relates to an aircraft glass antistatic structure.

Background

The transparent part of the aircraft cockpit is used as a component of the airtight cabin structure, provides a good observation view for a pilot in various flight states such as take-off, landing, cruising, taxiing and the like of the aircraft, and protects the pilot from the threat of collision of other flying objects. Usually, a "Z-bar", i.e. a metal pressure plate, is arranged at the outer glass edge of the transparent member to achieve the purpose of protecting the outer glass edge of the transparent member and preventing moisture from penetrating into the electric heating system of the transparent member of the cockpit.

However, in the flight process of the aircraft in service, charges in the air can be attached to the surface of glass to generate an electrostatic phenomenon, and part of charges can migrate to Z-bar, so that a discharge phenomenon can be generated between the end part of the Z-bar and a metal window frame of the aircraft body. Through long-time effect, can lead to transparent piece limit portion structure to be broken down and burn out, and then lead to steam invasion, make heating system take place the short circuit inefficacy, can lead to glass burst under the serious condition, influence aircraft flight safety.

To reduce the effect of static electricity on the transparent member, the Z-bar is grounded to reduce the failure probability, but the requirement on the edge of the transparent member is higher, and the Z-bar is not easy to be grounded, so that an antistatic structure is designed to reduce the failure probability.

Disclosure of Invention

In view of the above, the technical problem to be solved by the present utility model is to provide an antistatic structure for aircraft glass, which is used for avoiding the trouble of failure probability caused by static electricity in the flight process of the conventional aircraft cockpit transparent member.

In order to solve the technical problems, the utility model discloses an aircraft glass antistatic structure, which comprises:

the aircraft glass body is arranged as electric heating glass and is provided with outer layer glass, inner layer glass and an electric heating module, wherein the outer layer glass is adhered to the central surface of the inner layer glass through a film layer, the electric heating module comprises a resistance wire and a controller which are arranged between the outer layer glass and the inner layer glass, and the back surface of the inner layer glass is provided with a filler for supporting;

the transparent conductive film layer is plated on the outer surface of the outer glass layer;

one end of the Z-shaped metal pressing plate is in pressure connection with the outer edge of the outer layer glass, and the other end of the Z-shaped metal pressing plate extends to the outer edge of the inner layer glass;

an elastic conductor adhered to the outer surface of the filler;

the metal net is connected with the Z-shaped metal pressing plate and the elastic conductor;

the edge of the aircraft glass body is covered by sealant, the sealant covers the Z-shaped metal pressing plate, the metal net and the filler, and the lower end of the elastic conductor is exposed.

According to an embodiment of the present utility model, the lower end of the elastic conductor is pressed against the body sash.

According to an embodiment of the present utility model, the transparent conductive film layer is connected to the Z-type metal pressure plate through metal foil paper or conductive adhesive.

According to an embodiment of the present utility model, the metal mesh is connected to the Z-type metal pressing plate and the elastic conductor through conductive glue.

According to an embodiment of the present utility model, the elastic conductor is a conductive silica gel.

According to an embodiment of the present utility model, the Z-type metal platen encloses an aircraft glass body, and a sealant is filled between the Z-type metal platen and the aircraft glass body.

According to an embodiment of the present utility model, a height of the elastic conductor exposed out of the sealant is 1.5-2.5mm.

Compared with the prior art, the utility model can obtain the following technical effects:

the transparent conductive film layer, the Z-shaped metal pressing plate, the metal net and the elastic conductor are connected with the machine body, so that the grounding of the Z-shaped metal pressing plate is realized, the discharge phenomenon between the edge of the Z-shaped metal pressing plate and the frame of the machine body is avoided, and the probability of failure of the transparent part of the aircraft cockpit due to the electrostatic effect in the flight process can be reduced.

Of course, it is not necessary for any one product embodying the utility model to achieve all of the technical effects described above at the same time.

Drawings

The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the utility model and do not constitute a limitation on the utility model. In the drawings:

fig. 1 is a schematic view of an antistatic structure of aircraft glass according to an embodiment of the utility model.

Reference numerals

Outer layer glass 10, inner layer glass 20, filler 30, transparent conductive film layer 40, Z-shaped metal pressing plate 50, elastic conductor 60, metal mesh 70 and sealant 80.

Detailed Description

The following detailed description of embodiments of the present utility model will be given with reference to the accompanying drawings and examples, by which the implementation process of how the present utility model can be applied to solve the technical problems and achieve the technical effects can be fully understood and implemented.

Referring to fig. 1, fig. 1 is a schematic view of an antistatic structure of aircraft glass according to an embodiment of the utility model.

As shown, an aircraft glass antistatic structure, comprising: the aircraft glass body is arranged as electric heating glass and is provided with outer layer glass 10, inner layer glass 20 and an electric heating module, wherein the outer layer glass 10 is adhered to the central surface of the inner layer glass 20 through a film layer, the electric heating module comprises a resistance wire and a controller which are arranged between the outer layer glass 10 and the inner layer glass 20, and a filler 30 for supporting is arranged on the back surface of the inner layer glass 20; a transparent conductive film layer 40, wherein the transparent conductive film layer 40 is plated on the outer surface of the outer glass 10; a Z-shaped metal pressing plate 50, wherein one end of the Z-shaped metal pressing plate 50 is pressed and connected with the outer edge of the outer layer glass 10, and the other end extends to the outer edge of the inner layer glass 20; an elastic conductor 60, the elastic conductor 60 being adhered to the outer surface of the filler 30; a metal mesh 70, the metal mesh 70 connecting the Z-shaped metal platen 50 and the elastic conductor 60; the edge of the aircraft glass body is covered by the sealant 80, the sealant 80 covers the Z-shaped metal pressing plate 50, the metal mesh 70 and the filler 30, the lower end of the elastic conductor 60 is exposed, and the filler 30 is a rigid support of the glass structure.

In one embodiment of the utility model, the aircraft glass body is an aircraft cockpit transparency, incorporating an electrical heating system comprising an outer glass 10 and an inner glass 20. The inner glass 20 is not limited to single-layer glass according to the requirements of the aircraft windshield structure, and can be designed into an integrated structure of multiple layers of glass and organic films according to different strength and use requirements; the electric heating system is positioned in the middle interlayer, and a control wire of the heating system is led out of the glass and is connected with the control system.

The transparent conductive film layer 40 is plated on the outer surface of the outer layer glass 10, the section of the Z-shaped metal pressing plate 50 is Z-shaped, the Z-shaped metal pressing plate is lapped on the edge end part of the aircraft glass body, the Z-shaped metal pressing plate 50 and the transparent conductive film layer 40 are lapped on the edges of the outer layer glass 10 and the inner layer glass 20 in sequence, the assembly is completed, and the Z-shaped metal pressing plate 50 and the transparent conductive film layer 40 are stuck and indirectly contacted and conducted through conductive glue or aluminum foil paper, so that the continuity of conduction is realized. The elastic conductor 60 is adhered and fixed on the bottom surface of the filler 30, and is electrically connected with the Z-shaped metal pressing plate 50 through the metal net 70, and finally, the edge-wrapping protection is formed by using the sealant 80, so that the structural main body of the glass is formed.

The lower end of the elastic conductor 60 is pressed against the body sash. When the glass is installed on the machine body, the elastic conductor 60 and the frame of the machine body are mutually extruded to realize the conduction with the machine body, and then the grounding of the Z-shaped metal pressing plate 50 is realized.

When charges accumulated on the surface of the outer glass 10 generate static electricity in the flight process of the aircraft, the charges migrate to the Z-shaped metal pressing plate 50, and the charges can not be accumulated on the Z-shaped metal pressing plate 50 through the combined action of the whole anti-static structure, so that the discharge phenomenon between the edge of the Z-shaped metal pressing plate 50 and the frame of the aircraft fuselage is avoided, and the probability of failure of the transparent part of the cockpit of the aircraft due to the static electricity in the flight process can be reduced.

In a preferred embodiment, the transparent conductive film layer 40 is connected to the Z-type metal pressing plate 50 by metal foil paper or conductive adhesive to enhance the antistatic function, so as to realize conduction with the Z-type metal pressing plate 50 and further realize grounding.

In addition, the metal mesh 70 is connected with the Z-shaped metal pressing plate 50 and the elastic conductor 60 through conductive glue, so that the bonding is stable and the electric connection is convenient.

In a preferred embodiment, the elastic conductor 60 is made of conductive silica gel, which is convenient to use and stable in extrusion deformation. Further, the height of the exposed sealant 80 of the elastic conductor 60 is 1.5-2.5mm, and the sealant is fully extruded to complete grounding protection, and the height is finely adjusted according to the actual use environment.

The Z-shaped metal pressing plate 50 is surrounded by the aircraft glass body, and the sealant 80 is filled between the Z-shaped metal pressing plate and the aircraft glass body, so that the reinforced end part is stable, the assembly is more convenient and practical, and the structural main body of the glass is formed.

In summary, the transparent conductive film layer 40, the Z-shaped metal pressing plate 50, the metal mesh 70 and the elastic conductor 60 are conducted with the airframe, so that the grounding of the Z-shaped metal pressing plate 50 is realized, the discharge phenomenon between the edge of the Z-shaped metal pressing plate 50 and the airframe window frame is avoided, and the probability of failure of the transparent part of the aircraft cockpit due to the electrostatic action in the flight process can be reduced.

While the foregoing description illustrates and describes the preferred embodiments of the present utility model, it is to be understood that the utility model is not limited to the forms disclosed herein, but is not to be construed as limited to other embodiments, and is capable of numerous other combinations, modifications and environments and is capable of changes or modifications within the scope of the inventive concept as described herein, either as a result of the foregoing teachings or as a result of the knowledge or technology in the relevant art. And that modifications and variations which do not depart from the spirit and scope of the utility model are intended to be within the scope of the appended claims.

Claims

1. An aircraft glass antistatic structure, comprising:

the aircraft glass body is arranged as electric heating glass and is provided with outer layer glass, inner layer glass and an electric heating module, wherein the outer layer glass is adhered to the central surface of the inner layer glass through a film layer, the electric heating module comprises a resistance wire and a controller, the resistance wire and the controller are arranged between the outer layer glass and the inner layer glass, and a filler for supporting is arranged on the back surface of the inner layer glass;

the transparent conductive film layer is plated on the outer surface of the outer layer glass;

an elastic conductor bonded to the filler outer surface;

the edge of the aircraft glass body is covered by sealant, the sealant coats the Z-shaped metal pressing plate, the metal net and the filler, and the lower end of the elastic conductor is exposed.

2. The aircraft glass antistatic structure according to claim 1, wherein the lower end of the elastic conductor is pressed against the fuselage window frame.

3. The aircraft glass antistatic structure of claim 1, wherein the transparent conductive film layer is connected to the Z-type metal platen by metal foil paper or conductive adhesive.

4. The aircraft glass antistatic structure of claim 1, wherein the metal mesh is connected with the Z-shaped metal platen and the elastic conductor by conductive glue.

5. The aircraft glass antistatic structure of claim 1, wherein the elastic conductor is provided as a conductive silicone.

6. The aircraft glass antistatic structure according to claim 1, wherein the Z-shaped metal platen encloses the aircraft glass body and the sealant is filled between the Z-shaped metal platen and the aircraft glass body.

7. The aircraft glass antistatic structure according to claim 1, wherein the height of the elastic conductor exposing the sealant is 1.5-2.5mm.