KR101271011B1 - Anti-inflection window for air-plane display apparatus - Google Patents

Abstract

The present invention relates to a non-reflective window for an aircraft display device, and to block electromagnetic waves generated from the display device, to prevent the occurrence of moisture due to changes in altitude and pressure, and to maintain the normal operation of the display device at low temperatures. Of course, the visibility is prevented from being degraded by light incident from the outside, thereby providing an advantage of enabling safe air navigation.

Description

Anti-reflection window for air-plane display apparatus

The present invention relates to an anti-reflective window for an aircraft display device, and more particularly, to block electromagnetic waves generated from the display device and to prevent moisture from occurring due to changes in altitude and pressure, as well as at low temperatures. The present invention relates to a non-reflective window for an aircraft display device that allows the display device to operate well and prevents visibility from being degraded by light incident from the outside, thereby enabling safe air navigation.

In general, a display device such as a monitor or a television forms an image using a cathode ray tube (CRT), a liquid crystal display (LCD), or the like.

Such display devices generate electromagnetic waves, which cause harmful effects on the human body and cause electromagnetic interference (EMI), which causes malfunctions of various electronic devices in the vicinity. Electromagnetic interference is one of the most important issues, especially in the aviation field where high communication sensitivity must be maintained.

Multi functional display of avionics, that is, display device that displays navigation and flight information necessary for flight, prevents light incident from outside the cockpit from reflecting off the instrument surface and keeps the displayed image clear. It serves as a user interface between the aircraft and the pilot by maintaining accurate information delivery and improving visibility to pilots who need to make intuitive decisions in a short time ahead of complex instruments.

LCD panels are widely used in the multi-function display of such avionics, and the aviation display device has to solve the electromagnetic interference that causes malfunction of other avionics due to the electromagnetic waves generated from the display, In addition, due to the nature of the aircraft operating at a high altitude, the temperature in the cabin is very low, it is necessary to ensure that the liquid crystal of the display device, in particular, the LCD panel.

In addition, there is a need to solve the problem of blurring the pilot's view by reflecting from the outside surface of the display device by light incident from the outside into the cockpit during flight.

The present invention has been made to solve the above technical problem, and in addition to blocking the electromagnetic waves generated from the display device, and prevents the generation of moisture due to the altitude change and pressure change, and the display device works well at low temperatures An object of the present invention is to provide a non-reflective window for an aircraft display device that prevents visibility from being deteriorated by light incident from the outside, thereby enabling safe air navigation.

The anti-reflective window for an aircraft display device according to the present invention includes a glass substrate, a plurality of first antireflection layers stacked on one surface of the glass substrate, and a plurality of second stacked on the other surface of the glass substrate. An anti-reflection layer, an electromagnetic shielding layer laminated on one surface of the glass substrate with the plurality of first anti-reflection layers interposed therebetween, and a heater filter layer laminated on the other surface of the glass substrate with the second anti-reflection layer interposed therebetween. do.

The anti-reflective window for an aircraft display device according to the present invention blocks electromagnetic waves generated from the display device, thereby preventing malfunction of other avionics equipment, preventing moisture, and allowing the display device to operate normally at cryogenic temperatures.

1 is an exploded perspective view showing a state before the anti-reflection window for an aircraft display device according to the present invention is disposed on the front of the display,
2 is a cross-sectional view taken along line AA of FIG. 1,
FIG. 3 is a cross-sectional view taken along line AA of FIG. 1 and is a cross-sectional view showing another example of a light leakage preventing gasket layer.
4 is a cross-sectional view showing a state of being coupled to the display housing,
5 is a plan view showing a front surface of an anti-reflective window for an aircraft display device according to the present invention in the direction B of FIG.
FIG. 6 is a bottom view illustrating the bottom of an anti-reflective window for an aircraft display device according to the present invention in the direction C of FIG. 1.

Hereinafter, a preferred embodiment of an anti-reflective window for an aircraft display device according to the present invention will be described in detail with reference to the accompanying drawings.

1 is an exploded perspective view showing a state before the anti-reflection window for an aircraft display device according to the invention is disposed on the front of the display, Figure 2 is a cross-sectional view taken along the line AA of Figure 1, Figure 3 is a line AA of Figure 1 FIG. 4 is a cross-sectional view showing another example of a light leakage preventing gasket layer, and FIG. 4 is a cross-sectional view showing a state of being coupled to a display housing.

One preferred embodiment of the anti-reflective window 1 for an aircraft display device according to the invention is, for example, attached to an LCD panel (front of the display 10) constituting the display device, as shown in FIG. 1. As a window structure, as shown in FIG. 2, a glass substrate 20 and a plurality of first anti-reflection layers 30 and glass substrates 20 stacked on one surface of the glass substrate 20 are laminated. A plurality of second antireflection layers 40 stacked on the other surface, an electromagnetic wave shielding layer 50 laminated on one surface of the glass substrate 20 with a plurality of first antireflection layers 30 interposed therebetween, and a glass substrate ( The heater filter layer 60 stacked on the other surface of the substrate 20 with the second anti-reflection layer 40 interposed therebetween.

Here, the glass substrate 20 may be provided with tempered glass by glass reinforcement treatment to improve the strength.

The heater filter layer 60 is disposed on the other surface of the glass substrate 20 and serves as a heater for heating the glass substrate 20. The heater filter layer 60 is a low resistance transparent electrode so that the entire surface of the display 10 may be observed from the outside. It is provided. The material of the heater filter layer 60 may be indium-tin-oxide (ITO).

On the other hand, the front surface of the display 10 is coupled to the surface of the heater filter layer 60 in which the plurality of second anti-reflection layers 40 are not disposed, the anti-reflection window 1 for the aircraft display device and the display according to the present invention. (10) A bonding medium layer 70 which mediates inter-front bonding is laminated.

The coupling medium layer 70 is disposed between the front surface of the display 10 and the heater filter layer 60 to bond the front surface of the display 10 to each other by an optical bonding method. In particular, the coupling medium layer 70 is a portion where the front surface of the display 10 is coupled, and may be provided to adjust the reflectance through refractive index matching of the junction.

The coupling medium layer 70 prevents the pilot from causing glare by reflecting light incident from the outside of the cockpit of the aircraft by the front of the display 10, for example, the transmittance of an image (image) coming from the front of the display 10. In order to prevent the reflection of light incident from the outside, the height may be made of an anti-reflection coating (AR coating) layer.

To this end, the coupling medium layer 70 may be formed of a polymer film having an anti-reflection coating layer formed on the heater filter layer 60 by a lamination process, or directly made of titanium dioxide by vacuum deposition equipment.

The coupling medium layer 70 stacked in such a manner is different from only the names of the third anti-reflection layers 80 to be described later, which require a function of reducing the reflection of light incident from the outside. Can be.

In particular, the coupling medium layer 70 may be formed of an index matching coating layer for refractive index matching as described above, and the index matching coating layer may be formed of, for example, titanium dioxide and magnesium fluoride.

On the other hand, the electromagnetic wave shielding layer 50 is disposed on one surface, that is, the front surface of the glass substrate 20 to block the electromagnetic waves generated from the display 10 to serve as an EMI filter, and to capture and ground electromagnetic waves. For smoothness, it may be made of an EMI mesh film having an electrically conductive mesh structure.

According to an exemplary embodiment of the anti-reflective window 1 for an aircraft display device according to the present invention, as shown in FIG. 2, the third reflection is provided with an electromagnetic shielding layer 50 interposed between one surface of the glass substrate 20. The prevention layer 80 is laminated.

As described above, the third anti-reflection layer 80 is provided in the same manner as the coupling medium layer 70, and prevents glare of the pilot by preventing reflection of light incident from the outside of the cockpit of the aircraft.

5 is a plan view showing the front surface of the anti-reflective window for aircraft display device according to the present invention in the direction B of Figure 1, Figure 6 is a non-reflective window for aircraft display device according to the present invention in the direction C of Figure 1 Bottom view showing the bottom.

At the edge portion of the coupling medium layer 70, as shown in FIG. 6, a heater bus bar 90 connected to the heater filter layer 60 is disposed. The heater bus bar 90 is disposed to heat the heater filter layer 60 by supplying power to the heater filter layer 60. The heater bus bar 90 is connected to the power line by soldering or the like. It may be made of a conductive material such as copper (Cu).

In addition, as illustrated in FIG. 5, an electromagnetic shielding bus bar 100 connected to the electromagnetic shielding layer 50 may be disposed at an edge portion of the third antireflection layer 80. The electromagnetic shielding bus bar 100 may be connected to the electromagnetic shielding layer 50, as shown in FIG. 2. The electromagnetic shielding bus bar 100 is preferably grounded to process electromagnetic waves absorbed by the electromagnetic shielding layer 50. Through this, the electromagnetic wave generated by the driving of the display 10 device is blocked. The electromagnetic shielding bus 100 may be silver plated to increase electrical conductivity.

Here, the electromagnetic wave shielding bus bar 100 preferably surrounds the outside of the electromagnetic wave shielding layer 50 in order to efficiently discharge the electromagnetic wave absorbed by the electromagnetic wave shielding layer 50 to the ground.

On the other hand, in the anti-reflective window 1 for aircraft display device according to the present invention, on the edges of the plurality of second anti-reflection layer 40, a light leakage preventing gasket layer for preventing light leakage of light generated from the front of the display 10 110 may be disposed.

As shown in FIG. 3, the light leakage preventing gasket layer 110 may extend to surround the edge of the glass substrate 20 to prevent light leakage toward the side of the glass substrate 20. In addition, the other end 113 may be formed to extend to surround the edge of the heater filter layer 60 to prevent leakage of light toward the side of the heater filter layer 60.

The anti-reflective window 1 for an aircraft display device according to the present invention having such a configuration, as shown in FIG. 4, has an electromagnetic shielding layer inside the display housing 200 constituting the exterior of the display 10 device. 50) can be installed so as not to be exposed. In particular, the electromagnetic shielding bus bar 100 may be in contact with the housing 200, and may be grounded by at least a portion of the portion in contact with the housing 200. In this case, it is not necessary to bond an electric wire or the like to the electromagnetic shielding bus bar 100 for grounding.

On the other hand, a preferred embodiment of the non-reflective window (1) for the aircraft display device according to the present invention, in order to effectively prevent the reflection of the light incident from the outside of the cockpit, the light through the first third anti-reflection layer (80) After the reflection of light is reduced, the first and second antireflection layers 30 and 40 are provided on one and the other surfaces of the glass substrate 20, which are easy to reflect, to reflect the light. Configured to further reduce.

In addition, in a preferred embodiment of the anti-reflective window 1 for an aircraft display device according to the present invention, the plurality of first anti-reflection layer 30 and the plurality of second anti-reflection layer 40, at least two transmission layers ( 31, 33, 41, 43 are arranged in succession.

The transmissive layer and the third antireflective layer 80 of the plurality of first antireflective layers 30 and the second antireflective layer 40 are provided to transmit light having different wavelength bands, respectively. Here, the wavelength band of the transmitted light may be selected as a specific wavelength band of the light causing glare at a high altitude due to the operating characteristics of the aircraft.

In the above, a preferred embodiment of an anti-reflective window for an aircraft display device according to the present invention has been described in detail with reference to the accompanying drawings. However, it should be understood that the embodiments of the present invention are not limited to the above-described preferred embodiments, and that various modifications and equivalents may be made by those skilled in the art to which the present invention pertains will be. Therefore, it is to be understood that the true scope of the present invention is defined by the appended claims.

1: non-reflective window 10: display
20: glass substrate 30: first antireflection layer
40: second antireflection layer 50: electromagnetic shielding layer
60: heater filter layer 70: coupling medium layer
80: third antireflection layer 90: heater bus bar
100: electromagnetic wave shield bus bar 110: leakage prevention gasket layer
200: display housing

Claims (13)

Glass-substrate;
A plurality of first antireflection layers stacked on one surface of the glass substrate and a plurality of second antireflection layers stacked on the other surface of the glass substrate;
An electromagnetic shielding layer stacked on one surface of the glass substrate with the plurality of first anti-reflection layers interposed therebetween; And
And a heater filter layer stacked on the other surface of the glass substrate with the plurality of second anti-reflection layers interposed therebetween. The method of claim 1,
A non-reflective window for an aircraft display device further comprising a coupling medium layer laminated on the heater filter layer to mediate the coupling of the non-reflective window to the front surface of the aircraft display device. 3. The method of claim 2,
The coupling medium layer is a non-reflective window for an aircraft display device, characterized in that consisting of an index matching coating layer for increasing the light transmittance of the light incident from the outside to reduce the reflection. 3. The method of claim 2,
An anti-reflection window for an aircraft display device in which the bonding medium layer and the front surface of the aircraft display device are optically bonded. The method of claim 1,
An anti-reflection window for an aircraft display device further comprising a third anti-reflection layer laminated on one surface of the glass substrate with the electromagnetic shielding layer interposed therebetween. 3. The method of claim 2,
And a heater bus bar disposed at an edge of the coupling medium layer and connected to the heater filter layer. The method of claim 5, wherein
An anti-reflection window for an aircraft display device further comprising an electromagnetic shielding bus bar connected to the electromagnetic shielding layer disposed at an edge of the third antireflection layer. The method of claim 7, wherein
And the electromagnetic shielding bus bar is grounded. The method of claim 7, wherein
And the shielded bus bar is silver plated. 3. The method of claim 2,
And an anti-glare gasket layer disposed on an edge portion of the plurality of second anti-reflection layers to prevent light leakage of light generated from the front surface of the display. 11. The method of claim 10,
The light leakage preventing gasket layer is formed to extend to surround the edge of the glass substrate, the anti-reflection window for the aircraft display device. 11. The method of claim 10,
The light leakage preventing gasket layer is formed to extend to surround the edge of the heater filter layer, the anti-reflection window for the aircraft display device. The method of claim 5, wherein
The plurality of first anti-reflection layers and the plurality of second anti-reflection layers are each sequentially stacked in at least two transmission layers,
At least two transmissive layers of the plurality of first antireflection layers, at least two transmissive layers of the plurality of second antireflection layers, and the third antireflective layer each transmit a light having a wavelength band different from each other. Reflective windows.

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