JP2012116481A - Window member for aircraft and method for manufacturing the same - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a window member for aircraft having superior durability, and to provide a method for manufacturing the same.SOLUTION: The window member for aircraft includes: a film 5 made of an acrylic resin; a conductive mesh 7 that is formed on the film 5, has light permeability for securing visibility and is formed into a mesh-shape with a conductive material so as to have electromagnetic shielding property; and a window body 3 made of an acrylic resin, to which the film 5 formed with the conductive mesh 7 is attached.

Description

The present invention relates to an aircraft window material and a method for manufacturing the same.

  Aircraft window materials such as canopies and cabin windows are frequently used in order for aircraft occupants and passengers to ensure visibility outside the aircraft. In order to prevent harmful electromagnetic waves from entering from outside the aircraft or to prevent electromagnetic waves generated inside the aircraft from leaking out of the aircraft, it is considered to secure electromagnetic shielding properties for such aircraft window materials. ing.

  As an aircraft window member having such an electromagnetic wave shielding property, one described in Patent Document 1 is known. This document discloses a manufacturing method in which a metal mesh for electromagnetic wave shielding is formed on a film and then attached to a window body.

Japanese Patent Laying-Open No. 2005-104310 (FIG. 5)

However, when PET (polyethylene terephthalate), which is generally used as a resin film, is applied to the aircraft window as described above, there are the following problems.
Acrylic resin is used for the window body of aircraft window materials, and the difference in thermal expansion coefficient between acrylic resin and PET is large. Accordingly, when heat treatment is performed after a film is attached to the window body, wrinkles may occur based on the difference in coefficient of thermal expansion. Further, when the aircraft is operated, there is a large temperature difference between the ground and the navigation, and the film may be peeled off from the window body, which is not preferable from the viewpoint of durability.

  This invention is made | formed in view of such a situation, Comprising: It aims at providing the window material for aircraft excellent in durability, and its manufacturing method.

In order to solve the above problems, the aircraft window material of the present invention and the manufacturing method thereof employ the following means.
That is, the aircraft window material of the present invention comprises a film made of an acrylic resin, and a conductive material formed on the film so as to have light transmittance for ensuring visibility and to have electromagnetic wave shielding properties. A conductive mesh formed in a mesh shape and an acrylic resin window main body to which the film on which the conductive mesh is formed are attached.

  Since the window main body and the film are made of acrylic resin, the coefficients of thermal expansion are equal. Therefore, even if heated and cooled during production, wrinkles are unlikely to occur. Aircraft window materials are exposed to large temperature changes during aircraft operation, but there is no difference in the coefficient of thermal expansion between the window body and the film. Improves.

  Further, in the aircraft window material of the present invention, an adhesive layer is formed between the film on which the conductive mesh is formed and the window body, and the adhesive layer is a urethane-based adhesive. It is characterized by that.

  In laminated glass used for automobiles and the like, PVB (polyvinyl butyral) is generally used as an adhesive, but PVB is not preferable in terms of adhesive strength with an acrylic resin. On the other hand, the urethane-based adhesive has a sufficient adhesive force when bonding an acrylic resin film and an acrylic resin window body. As the urethane adhesive applied to the present invention, it is preferable to use a film-like polyurethane.

  Furthermore, according to the aircraft window material of the present invention, the conductive mesh formed on the film is disposed between the film and the window body.

  Since the conductive mesh formed on the film is disposed between the film and the window body, the conductive material of the conductive mesh and the adhesive layer are in direct contact. The adhesive layer uses a urethane-based adhesive and does not contain a plasticizer like PVB, so there is no reaction between the conductive material of the conductive mesh and the adhesive layer, and light is transmitted as a window material. Does not adversely affect sex.

  Furthermore, in the aircraft window material according to the present invention, the conductive mesh is positioned on the window body via the film, and the conductive mesh is electrically connected to the edge of the conductive mesh on the conductive mesh. The protective layer is formed in a state where the exposed region is provided.

  When the conductive mesh formed on the film does not face the window body and is positioned on the opposite side of the window body through the film, a protective layer for protecting the conductive mesh is laminated. There is a need. When the protective layer is laminated, an exposed region that is not covered with the protective layer is provided at the edge of the conductive mesh. By using this exposed region for electrical connection, electrical connection for electromagnetic wave shielding can be ensured.

  In addition, an aircraft window assembly of the present invention includes the aircraft window material according to any one of the above and a window frame that holds the aircraft window material.

  By providing any of the aircraft window materials described above, an aircraft window assembly having excellent durability can be provided.

  Further, the aircraft window material manufacturing method of the present invention is an acrylic that holds a conductive mesh in which a conductive material is formed in a mesh shape so as to have a light transmission property for ensuring visibility and an electromagnetic wave shielding property. A resin film is attached to a window body made of acrylic resin.

Since it is only necessary to attach a film to the window body, it can be easily manufactured. Even if the window body has a curved surface, the film has flexibility, so that the film can be attached easily.
Since the window main body and the film are made of acrylic resin, the coefficients of thermal expansion are equal. Therefore, even if heated and cooled during production, wrinkles are unlikely to occur. Aircraft window materials are exposed to large temperature changes during aircraft operation, but there is no difference in the coefficient of thermal expansion between the window body and the film. Improves.

  Furthermore, the aircraft window material manufacturing method of the present invention is characterized in that an adhesive layer made of a urethane-based adhesive is provided on the window main body, and then the film is attached to the window main body.

  In laminated glass used for automobiles and the like, PVB (polyvinyl butyral) is generally used as an adhesive, but PVB is not preferable in terms of adhesive strength with an acrylic resin. On the other hand, the urethane-based adhesive has a sufficient adhesive force when bonding an acrylic resin film and an acrylic resin window body.

  Furthermore, the aircraft window material manufacturing method of the present invention is characterized in that the film is affixed to the window body so that the conductive mesh is disposed between the film and the window body. To do.

  Since the conductive mesh formed on the film is disposed between the film and the window body, the conductive material of the conductive mesh and the adhesive layer are in direct contact with each other. The adhesive layer uses urethane adhesive and does not contain plasticizer like PVB, so there is no reaction between the conductive material of the conductive mesh and the adhesive layer. Does not adversely affect

  Furthermore, in the method for manufacturing an aircraft window material according to the present invention, the conductive mesh is attached to the window main body so that the conductive mesh is positioned on the window main body via the film. A protective layer is formed on the edge of the conductive mesh so as to provide an exposed region for electrical connection.

  Since the exposed region for electrical connection is provided at the edge of the conductive mesh, electrical connection for electromagnetic wave shielding can be ensured.

The present invention has the following effects.
Since the window body and the film are made of acrylic resin, a highly durable aircraft window material can be provided.
Since the film and the window main body are bonded using a urethane-based adhesive, it can be firmly bonded. Further, even when the adhesive layer and the conductive film layer are in direct contact with each other, the light transmittance for ensuring visibility is not reduced.
When the protective layer is laminated on the conductive mesh, an exposed region is provided at the edge of the conductive mesh to obtain an electrical connection, so that electromagnetic wave shielding can be performed reliably.

It is the perspective view which showed the window material for aircraft concerning one Embodiment of this invention. It is a fragmentary sectional view in the edge part of the window material for aircrafts of FIG. It is sectional drawing which showed a part of manufacturing process of the window material for aircrafts of FIG. It is a fragmentary sectional view in the edge part of the window material for aircraft concerning a 2nd embodiment of the present invention.

Embodiments according to the present invention will be described below with reference to the drawings.
[First Embodiment]
Hereinafter, a first embodiment of the present invention will be described with reference to FIGS.
FIG. 1 shows an aircraft window material used for, for example, a cabin window. Although the aircraft window member 1 shown in FIG. 1 has a flat plate shape, it has a curved surface shape according to the position to which it is applied.
The aircraft window material 1 includes a window main body 3 serving as a substrate, a film 5 attached on the window main body 3, and a conductive mesh 7 formed on the film 5. The aircraft window material 1 has an electromagnetic wave shielding property due to the conductive mesh 7 and also has a light transmittance for securing a field of view. For example, the visible light transmittance is about 90%.

FIG. 2 shows a partial cross section at the end of the aircraft window material 1.
As shown in the figure, a conductive mesh 7 and a film 5 are laminated in this order on the window body 3 with an adhesive layer 9 interposed.
The window main body 3 is made of acrylic resin, more specifically, PMMA (methyl methacrylate resin).
The film 5 is made of acrylic resin, more specifically, PMMA (methyl methacrylate resin). That is, a material equivalent to that of the window body 3 is used for the film 5. The thickness of the film 5 is, for example, 125 μm.
The conductive mesh 7 is formed in a lattice shape, and a metal is preferable as the conductive material, and copper is used in this embodiment. The conductive mesh 7 has a line width of about 10 μm, a thickness of about 10 μm, and an interval of about 300 μm. With such a line width, thickness, and interval, both electromagnetic shielding properties and ensuring visibility are achieved.
The adhesive layer 9 is a urethane adhesive. As the urethane-based adhesive, film-like polyurethane is used. After bonding, the adhesive layer 9 enters the space between the film 5 and the conductive mesh, and directly contacts the conductive mesh 7 so as to cover the conductive material (copper).

Next, a method for manufacturing the aircraft window material 1 having the above configuration will be described.
First, a copper thin film is laminated on one surface of the film 5 by, for example, a plating method. The thickness of the copper thin film is, for example, 10 μm. Then, a resist film is formed on the surface of the copper thin film, and then a resist pattern is exposed on the resist film and then developed to form a mesh-shaped mask on the surface of the copper thin film. In this state, copper is etched with an etching solution, and then the resist pattern is removed, thereby forming a mesh-shaped conductive mesh 7. In this way, the film 5 with the conductive mesh 7 is obtained as indicated by reference numerals 5 and 7 in FIG.
And after installing the contact bonding layer 9 made into the sheet-like urethane adhesive on the window main body 3, the film 5 is stuck so that the electroconductive mesh 7 may oppose the window main body 3. FIG.
Next, heat treatment is performed using an autoclave to cure the adhesive layer 9 and fix the film 5 on the window body 3. As processing conditions by the autoclave, the temperature is 85 to 95 ° C., the pressure is 1.03 MPa, and the processing time is 1 hour.
And the window material 1 for aircrafts is obtained by taking out from an autoclave and cooling.
The aircraft window material 1 manufactured in this way is assembled to a window frame or the like later to obtain an aircraft window assembly.

The aircraft window member 1 according to the present embodiment has the following operational effects.
Since the aircraft window member 1 can be manufactured simply by attaching the film 5 on which the conductive mesh 7 is formed to the window main body 3, it is simple. Even if the window body 3 has a curved surface, the film 5 on which the conductive mesh 7 is formed has flexibility, so that the film 5 can be easily attached to the window body 3. .
Since the window main body 3 and the film 5 are made of acrylic resin and have the same thermal expansion coefficient, the film 5 is hardly wrinkled even if it is heated by an autoclave at the time of manufacture and then cooled.
Further, the aircraft window material 1 is exposed to a large temperature change as the aircraft is operated. However, since there is no difference in coefficient of thermal expansion between the window main body 3 and the film 5, the film is hardly peeled off. Thus, durability can be improved.
Further, since the urethane adhesive is used as the adhesive layer 9, the acrylic resin window body 3 and the film 5 can be firmly bonded.
In addition, since the urethane adhesive does not contain a plasticizer like PVB (polyvinyl butyral), it does not cause a reaction even if it directly contacts copper of the conductive mesh 7, and light as a window material. Does not adversely affect permeability.

[Second Embodiment]
Next, a second embodiment of the present invention will be described with reference to FIG.
FIG. 4 shows a partial cross section at the end of the aircraft window member 1 ′ according to the present embodiment.
In the present embodiment, unlike the first embodiment, when the film 5 on which the conductive mesh 7 is formed is attached to the window main body 3, the conductive mesh 7 is not opposed to the window main body 3 and is directed upward in FIG. 4. It is aimed. Therefore, the stacking order is the window main body 3, the adhesive layer 9, the film 5, and the conductive mesh 7 from below in FIG. About the window main body 3, the contact bonding layer 9, the film 5, and the electroconductive mesh 7, since it is the same as that of 1st Embodiment about material and a shape, the description is abbreviate | omitted.

A protective layer 11 for protecting the conductive mesh is laminated on the conductive mesh 7. As the protective layer 11, an acrylic resin film is used. Adhesion between the conductive mesh 7 and the protective layer 11 is performed with a polyvinyl acetate adhesive.
An exposed region 13 that is not covered with the protective layer 11 is provided at the edge of the conductive mesh 7. This exposed region 13 is for securing electrical connection with the outside when the aircraft window member 1 is attached to a window frame to form a window assembly.

The aircraft window member 1 ′ having the above-described configuration is manufactured as follows.
The process of forming the conductive mesh 7 on the film 5 is the same as that in the first embodiment, and is therefore omitted.
A protective layer 11 is pasted on the conductive mesh 7 formed on the film 5. Then, the film 5 on which the conductive mesh 7 is formed is pasted on the window body 3. At this time, the film 5 is adhered to the window body 3 on which the sheet-like adhesive layer 9 is placed, with the conductive mesh 7 facing upward in FIG. 4 without facing the window body 3 side. Contact layer 9.
Then, similarly to the first embodiment, the adhesive layer 9 is thermally cured by an autoclave and cooled, and then the aircraft window material 1 ′ is obtained.
The aircraft window member 1 ′ thus manufactured is later assembled to a window frame or the like to obtain an aircraft window assembly.

According to the aircraft window member 1 ′ according to the present embodiment, the following operational effects are obtained in addition to the operational effects of the first embodiment.
When the protective layer 11 is laminated on the conductive mesh 7, the exposed region 13 that is not covered with the protective layer 11 is provided at the edge of the conductive mesh 7, and this exposed region is used for electrical connection. be able to. Therefore, when the aircraft window member 1 ′ is assembled to the window frame to form an aircraft window assembly, electrical connection with the outside can be ensured, and electromagnetic wave shielding can be reliably performed.

  In each of the embodiments described above, copper is used as the material of the conductive mesh 7, but the present invention is not limited to this. For example, gold, silver, aluminum, nickel, titanium, and tin are used. There may be.

1,1 'Aircraft window material 3 Window body 5 Film 7 Conductive mesh 9 Adhesive layer 11 Protective layer 13 Exposed area

Claims (9)

A film made of acrylic resin,
A conductive mesh formed on the film, having a light transmittance for ensuring visibility and having an electromagnetic shielding property, and a conductive material formed in a mesh shape;
An acrylic resin window body to which the film on which the conductive mesh is formed is attached;
An aircraft window material characterized by comprising: An adhesive layer is formed between the film on which the conductive mesh is formed and the window body,
The aircraft window material according to claim 1, wherein the adhesive layer is a urethane-based adhesive.   The aircraft window material according to claim 2, wherein the conductive mesh formed on the film is disposed between the film and the window body. On the window body, the conductive mesh is located via the film,
The aircraft protective aircraft according to claim 1, wherein a protective layer is formed on the conductive mesh in a state where an exposed region for electrical connection is provided at an edge of the conductive mesh. Window material. An aircraft window member according to any one of claims 1 to 4,
A window frame for holding the aircraft window material;
An aircraft window assembly comprising:   Acrylic resin film that holds a conductive mesh with a conductive material formed in a mesh shape so that it has light transmission properties to secure visibility and electromagnetic shielding properties is affixed to an acrylic resin window body. A method for manufacturing an aircraft window material.   The method for manufacturing an aircraft window material according to claim 6, wherein an adhesive layer made of a urethane-based adhesive is provided on the window main body, and then the film is attached to the window main body.   The method for manufacturing an aircraft window material according to claim 7, wherein the film is attached to the window body so that the conductive mesh is disposed between the film and the window body. Affixing the film to the window body so that the conductive mesh is located on the window body via the film,
8. The aircraft window material according to claim 6, wherein a protective layer is formed on the conductive mesh so as to provide an exposed region for electrical connection at an edge of the conductive mesh. Method.

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