• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    AIRCRAFT COCKTAIL WINDOW HAVING ELECTROMAGNETIC SHIELDING, AND, AIRCRAFT An aircraft cockpit window is provided for the aircraft and the aircraft in which an electromagnetic shielding film to prevent electromagnetic noise can be reliably and easily provided at low cost. An electromagnetic shielding film (27) is provided in a window part (21), and a conductive film (41) is provided between the electromagnetic shielding film (27) and an external retainer (22) made of a conductive material. The conductive film (41) is connected to the electromagnetic shielding film (27) via a connecting member (40), it is provided so as to be guided to an outer perimeter side of the window part (21) along a part outer perimeter of the window part (21), and is electrically connected to the external retainer (22). With this configuration, a film made of a conductive material is formed without an interstice in a joint portion between the window part (21) and the external retainer (22). Also, the conductive film (41) is a flexible film.
    公开号:BR112012005536B1
    申请号:R112012005536-4
    申请日:2011-01-24
    公开日:2021-01-19
    发明作者:Takashi Yokoi
    申请人:Mitsubishi Aircraft Corporation；
    IPC主号:
    专利说明:

    Technical Field
    [001] The present invention relates to an aircraft cockpit window having an electromagnetic shield, and to the aircraft. Fundamentals of Technique
    [002] An aircraft must be able to fly safely without malfunction, unforeseen behavior (disturbance), or others in High Intensity Radiated Fields (HIRF), which represent an electromagnetic environment from radio, television, radar, emitters, and other sources during the cruise flight or during takeoff or landing. For this purpose, HIRF protection measures required in sections (14 CFR) 23.1308, 25.1317, 27.1317, and 29.1317 of the protection against High Intensity Radiated Fields (HIRF), which stipulate regulations (airworthiness requirements) of the Federal Aviation Administration ( FAA), must be taken.
    [003] The importance of protecting aircraft electrical / electronic systems has been significantly increasing in recent years for the following reasons: 1) a greater reliance on electrical / electronic systems that perform the functions required for the continued safe flight and landing of the aircraft; 2) a decrease in electromagnetic shielding by a composite material of some kind for use in aircraft design; 3) an increase in susceptibility (sensitivity) to HIRF of the accompanied electrical / electronic systems, accompanied by a higher speed of operation of a data collecting bar and a processor, a higher density of an IC and a card, and a greater degree sensitivity of electronic equipment; 4) an expansion of frequency usage to a high frequency band, in particular, 1 GHz and above; 5) an increase in the severity of an HIRF environment with an increase in the number of RF transmitters and electrical energy; and 6) an adverse effect on the part of the aircraft when exposed to the HIRF environment.
    [004] On the other hand, inside an aircraft, due to radio waves and electromagnetic noise (hereinafter simply referred to as electromagnetic noise) emitted by various electronic equipment, such as portable phones, game machines, personal computers of the type of notebook, and PEDs (Personal Electro Devices), such as an active type RFID tag (Radio Frequency Identification) affixed to the air cargo of goods, an adverse effect may occur in, for example, communications with a control and communications tower and navigation control for flight via a predetermined route. Thus, as is well known, passengers are asked to refrain from using various electronic equipment inside the aircraft.
    [005] Since an aircraft body is generally formed of metal, electromagnetic noise comes and goes from / to a cockpit (a seat space) to a flight deck (a flight deck) and an avionics compartment mainly through a cockpit window and a cockpit window. Thus, to prevent electromagnetic noise that can be an obstacle against entry into the flight deck and the avionics compartment, a film made of ITO (Indium-Tin Oxide), gold, silver, or similar, is provided as being inserted into the cabin window made by laminating a plurality of window panels made of acrylic or similar (for example, refer to Patent Document 1). Citation List
    [006] Patent Document
    [007] Patent Document 1: Publication of Unexamined Japanese Patent Application (PCT Application Translation) No. 2003-523911. Summary of the Invention Technical problems to be solved by the invention
    [008] On the other hand, in the cockpit window, a heater formed from a film also made of ITO, gold, silver, or similar, has already been inserted for antifreeze or defogging. Thus, it can be imagined that the film configuration of this heater is used to prevent electromagnetic noise from entering. In a part of the outer perimeter of the window, a retainer mounting frame made of metal is attached by a fastener to a window frame made of a metal (conductor) material provided on one side of the housing, thus mounting the cab window pilotage in the carcass. However, since the heating film is required to be electrically insulated, if an electrical space is present between the heating film and the mounting frame, electromagnetic noise enters the flight deck from this space. To prevent this entry, it is required that a connection be made reliably between the film and the fixing frame on this part. However, consideration is not given to this extent, because the technology set out in Patent Document 1 is directed towards a cabin window.
    [009] Also, the cockpit window includes a main windshield on one front side and side windows positioned on its sides. And, the film described above, is provided mainly for antifreeze on the main windshield and for defogging on the side windows. For this reason, a resistance value required for a defogging heater makes a heating film thin, and therefore a sufficient electromagnetic shielding attenuation effect cannot be obtained. In addition, although the cockpit window has at least one outer layer formed of glass, because a cleaner is used to clean raindrops and others, the other layers are not necessarily formed of glass, but can also be formed of acrylic. or similar.
    [0010] As such, the application of the film, the material of the window panels and their multilayer structure, and others, may be different between the main windshield and the side windows. Therefore, as described above, each connection between the film and the fixing frame has a dedicated structure on each of the main windshield and the side windows, leading to an increase in cost.
    [0011] Still additionally, to fix the plurality of window panels and fix them to the mounting frame, the outer perimeter part can be fixed with a fastener. Here, when the window panels are made of glass, in order to prevent a cracking in the window panels due to the fixing force of the fastener, a portion where the outer perimeter part of the window panels is fixed with the fastener it is formed of a softer material than glass (for example, a glass fiber). As a result, this portion is deformed by the fixing force of the fastener and, as a result, there is a possibility that the film may fall.
    [0012] The present invention is based on these technical problems, and has an objective of providing an aircraft cockpit window and the aircraft in which a film to prevent electromagnetic noise can be reliably and easily provided, at low cost. Solution to the Problem
    [0013] For this purpose, an aircraft cockpit window having an electromagnetic shield according to the present invention includes a plurality of transparent laminated window panels; an inner retainer on the inner side and an outer retainer on the outer side made of a conductive material, the retainers provided for an outer perimeter part of the window panels and interposing the window panels, a coupling member coupling the inner retainer and the retainer external to each other; a weather seal provided between the external retainer and the window panels; an electromagnetic shielding film provided between two of the window panels that are opposite each other and made of a conductive material; and a connecting film made of a conductive material and electrically connecting an external perimeter part of the electromagnetic shielding film and the external retainer.
    [0014] As such, by connecting the outer perimeter part of the electromagnetic shielding film provided between two opposite window panels and the external retainer made of conductive material with the connecting film, the electromagnetic shielding film and the external retainer can reliably become drivers.
    [0015] In addition, preferably, the connecting film has an end interposed between two of the window panels that are opposed to each other, to be electrically connected to the electromagnetic shielding film, and has another end connected to the external retainer outside the protection panels. window, and an intermediate part between one end and the other end is along an outer perimeter surface of the window panels and is provided to fill a space between the outer perimeter part of the electromagnetic shielding film and the retainer external. With this, electromagnetic noise can be prevented from entering from a space between the outer perimeter part of the electromagnetic shielding film and the external retainer.
    [0016] At this time, the electromagnetic shielding film can be provided on an internal perimeter side from a portion fixed by the internal retainer and the external retainer and the connecting film can be inserted into the portion. With this, the clamping force by the internal retainer and the external retainer can be prevented from acting on the electromagnetic shielding film, thus preventing the electromagnetic shielding film from falling out even in the case where the outer perimeter part of the window panel it is made of a softer material than glass.
    [0017] The connection film and the electromagnetic shielding film can be connected via a connecting member in the form of a strap, provided to surround the outer perimeter part of the electromagnetic shielding film, the connection member being made of a conductive material. Like this connecting member, a braided metal wire can be used.
    [0018] Still additionally, a heater layer for anti-freeze or anti-fog can still be provided among the plurality of window panels.
    [0019] The present invention can be directed to an aircraft that includes the cockpit window having the electromagnetic shielding as described above. Advantageous Effects of the Invention
    [0020] According to the present invention, with a simple structure so that the outer perimeter part of the electromagnetic shielding film provided between two panels that are opposite each other and the outer retainer made of the conductive material are connected with the film of connection, the space between the electromagnetic shielding film and the external retainer is electrically filled, and the entry of radio waves and electromagnetic noise from the space between the outer perimeter part of the electromagnetic shielding film and the external retainer can be prevented .
    [0021] Also, even when a portion of the outer perimeter part of the window panel to be fixed with the fastener is made of a material softer than glass, the electromagnetic shielding film can be prevented from falling out due to the force of fastener fixation.
    [0022] As such, the electromagnetic shielding film to prevent electromagnetic noise can be reliably and easily provided at low cost. Also, with the electromagnetic shielding film being interposed between the laminated window panels, failures due to dust, thrown stone, and others, and friction by a cleaner, do not have an influence, thus eliminating the need for maintenance at the time of maintenance. carcass. Brief Description of Drawings
    [0023] Figure 1 is a view of a cockpit portion of an aircraft in the present modality.
    [0024] Figure 2 is a sectional view showing a sectional structure of a cockpit window and its structure for mounting on a frame.
    [0025] Figure 3a is an enlarged sectional view of a connection portion between an electromagnetic shielding film and a conductive film, and figure 3B is an enlarged sectional view of a connection portion between the conductive film and an external retainer.
    [0026] Figure 4 is a view showing a sectional structure of a side window.
    [0027] Figure 5 is a view showing another example of the cockpit window. Description of the modality
    [0028] The present invention will now be described in detail on the basis of an embodiment shown in the attached drawings.
    [0029] Figure 1 is a view for describing the structure of a cockpit window 20 of an aircraft 10 in the present embodiment.
    [0030] As shown in figure 1, the cockpit window (main windshield) 20 is provided in front of an aircraft cockpit 10.
    [0031] As shown in figure 2, the cockpit window 20 is mounted in an opening 12 formed in a liner 11 configuring an aircraft housing 10. The cockpit window 20 has a window part 21 and a retainer outer 22 surrounding the entire perimeter of the outer perimeter part of the window part 21.
    [0032] The window part 21 is configured by laminating a plurality of, three in the present embodiment, window panels 23A to 23C. Here, in the cockpit window 20 as a main windshield, among the window panels 23A to 23C, at least the window panel 23A, which is a surface layer facing the outside of the aircraft body 10, is made of glass. In addition, in the present embodiment, all of the window panels 23A to 23C are made of glass.
    [0033] A resin film 24A is interposed between the window panels 23A and 23B and a resin film 24B is interposed between the window panels 23B and 23C, these resin films being made of PVB (polyvinyl butyral) or similar .
    [0034] Also, between the window panel 23A and the resin film 24A, a heater layer 25 made of a conductive material forming a heater for antifreeze is formed. This heater layer 25 is formed of a thin film made of a conductive material, such as ITO, gold, silver, or the like.
    [0035] In addition, between the heater layer 25 and the resin film 24A, an intermediate layer 26 made of urethane or the like is provided.
    [0036] Between the resin film 24A and the window panel 23B, an electromagnetic shielding film 27 is interposed. The electromagnetic shielding film 27 is a thin film formed of a conductive material such as ITO, gold, silver, or others.
    [0037] On external perimeter portions of the window panels 23B and 23C, spacers 28A and 28 B that have the same thickness as those of the window panels 23B and 23C, respectively, are provided so as to surround their entire perimeters. The spacers 28A and 28B are coupled to the window panels 23B and 23C with strips 29A and 29B, respectively, the strips being provided on the front and rear sides of each of the spacers 29A and 29B. Here, spacers 28A and 28B and strips 29A and 29B are made of fiberglass, for example.
    [0038] And, the spacers 28A and 28B and the resin film 24B project to an outer perimeter side with respect to the window panel 23A, the resin film 24A, the heater layer 25, and the electromagnetic shielding film 27.
    [0039] Between the outer perimeter part of the window part 21 and the outer retainer 22, as described above, specifically, on an outer perimeter part of a surface of the window panel 23A and in a portion along a surface of the window panel 23B projecting to the outer perimeter side of window panel 23A, a weather seal 31 made of a rubber-based material, resin, or the like, is provided. The weather seal 31 is provided so as to surround the entire outer perimeter part of the window part 21. The weather seal 31 has a cross-sectional shape in the form of a crank, formed from a portion 31a along the spacer 28A and the window panel 23B, a portion 31b rising along the perimeter surfaces of the resin film 24A and the window panel 23A, and a portion 31c along a surface of the window panel 23A. And, the weather seal 31 contains a Z retainer (a core material) 31Z also having a crank-shaped cross-sectional shape. The Z 31Z retainer is made of a non-conductive material, and can be made of, for example, fiberglass.
    [0040] In the portion projecting from the window panel 23A to the side of the outer perimeter, the weather seal 31, the spacers 28A and 28B, and the resin film 24B are interposed between the outer retainer 22 made of metal (a conductive material) and arranged outside and a seal 30 and an internal retainer 32 arranged inside. And, a through hole 33 is formed in this outer retainer 22, weather seal 31, spacer 28A, resin film 24B, spacer 28B, seal 30, and inner retainer 32. Through hole 33 has an internal perimeter surface on which a cylindrical sleeve 34 having a predetermined length adjusts, thus regulating a space between the outer retainer 22 and the inner retainer 32.
    [0041] And, with a fastener (a coupling member) 35 inserted in the through hole 33 and a washer 36 and a nut 37 mounted on a tip end part of a fastener 35 projecting from the internal retainer 32 to an aircraft interior, the weather seal 31, the window panels 23B and 23C, and the resin film 24B are retained and secured with the outer retainer 22 and the inner retainer 32.
    [0042] The external retainer 22 is attached to a stringer member 13 by configuring the aircraft housing 10 with a retaining member 14, such as a screw or rivet. This stringer member 13 is made of metal, which is a conductive material, with one side having the lining 11 attached to it and the other side having the outer retainer 22 attached to it via a sealing member.
    [0043] However, in the structure described above, the electromagnetic shielding film 27 is formed on an inner side (a central side) of the window part 21 from the portion fixed with the outer retainer 22 and the inner retainer 32. This is to prevent the electromagnetic shielding film 27 from falling due to a clamping force by the outer retainer 22 and the inner retainer 32. If the electromagnetic shielding film 27 is provided on an inner side from the portion fixed with the outer retainer 22 and the internal retainer 32, the clamping force by the external retainer 22 and the internal retainer 32 do not act directly on the electromagnetic shielding film 27.
    [0044] As shown in figure 2 and figure 3A, a connecting member in the form of a collecting bar 40 is provided on the outer edge of the electromagnetic shielding film 27 in order to surround its entire perimeter. This connecting member 40 is suitably formed of a flat braided metal wire, but it can be formed of any other conductive material. This connecting member 40 is provided so as to be interposed between a surface of the electromagnetic shielding film 27 and the resin film 24A, and is electrically connected to the electromagnetic shielding film 27 by welding or the like.
    [0045] Also, on one side of the outer perimeter of the connecting member 40, a conductive film (a connecting film 41) made of a material, such as Ag, Al, Ni, or Cu, and having flexibility, is provided with in order to surround the entire perimeter of the electromagnetic shielding film 27. The conductive film 41 has an end 41a electrically connected to the connecting member 40. In addition, the conductive film 41 is interposed between a surface of the window panel 23B and the seal against weather 31, and is guided so that it protrudes from the window part 21 to an external perimeter side.
    [0046] As shown in figure 3B, in the conductive film 41, a projection part (an intermediate part) 41b that projects from the window part 21 to an external perimeter side is provided so as to be curved in the direction to the outer retainer side 22 (an outer side of the housing) and along the outer perimeter part of the weather seal 31. This projection part part 41b is provided so as to surround the entire perimeter of the weather seal 31 and have its tip end part 41c without an interstice with respect to the outer retainer 22. When a corner of the weather seal 31 is shaped into a curve, the conductive film can be bent and cut and then another conductive film can be affixed to the external perimeter of the weather seal.
    [0047] The projection part 41b has a trough (the other end) 41d formed partly in its perimeter direction in order to protrude from it. The trough 41d is curved along one side of the rear surface of the outer retainer 22, and is electrically grounded (by gluing) to the outer retainer 22 with a fastener or the like. The grounded point is assumed to be a minimum point, but it can be completely around (peripheral) in order to improve the shielding capacity.
    [0048] According to the structure described above, the window part 21 is provided with an electromagnetic shielding film 27, and the conductive film 41 is provided between this electromagnetic shielding film 27 and the outer retainer 22 made of a conductive material . This conductive film 41 is provided so that it projects towards an outer perimeter side of the window portion 21 along the outer perimeter portion of the weather seal 31 (the window portion 21), and is electrically grounded to the outer retainer 22 With this, a film made of a conductive material can be formed without an electrical gap between the window part 21 and the external retainer 22 and in a joint part with the casing 11, and electromagnetic noise can be reliably prevented from enter the flight deck.
    [0049] At this moment, since the conductive film 41 has flexibility, this film can be prevented from falling even when the clamping force of the external retainer 22 and the internal retainer 32 act on the film. Also, the conductive film 41 which has flexibility, as described above, can be easily manipulated even when a portion projecting to an outer perimeter side of the window part 21 is curved along the outer perimeter part of the weather seal 31 .
    [0050] As such, the electromagnetic shielding film to prevent the entry of electromagnetic noise can be reliably and easily provided at low cost.
    [0051] Note that the structure as described above can be modified, when appropriate, without departing from the spirit of the present invention. An example of modification is now described below. Here, in the modification example below, a structure common to the structure described above is provided with the same reference signs, and its description is omitted.
    [0052] First, although the structure of the cockpit window 20 as a main windshield has been described above, the structure can also be applied to a side window 50 of the cockpit. Figure 4 is a view showing the structure when the present invention is applied to the side window 50 of the cockpit.
    [0053] As shown in figure 4, in the side window 50, the heater layer 25 is provided between the window panel 23C and the resin film 24B in order to be positioned further into the aircraft because it is used for defogging. Other structures are similar to those in the cockpit window 20 shown in figure 2.
    [0054] With this, the conductive film 41 is provided to the electromagnetic shielding film 27 via the connecting member 40 on the same layer and, in addition, the conductive film 41 is guided to the outer perimeter side of the weather seal 31 to be curved along the outer periphery part of the weather seal 31 and is electrically grounded to the outer retainer 22. The structure in which an electromagnetic shielding film is provided in order to prevent the entry of electromagnetic noise can be commonly used between the cockpit window 20 and side window 50. With this, an increase in production costs can be suppressed.
    [0055] Also, although the window panels 23B and 23C are made of glass in the structure described above, these can be made of acrylic. Figure 5 is a view of an example in which the window panels 23D and 23E are made of acrylic. In this case, spacers 28A and 28B are not provided, and the through hole 33 is directly formed in the window panels 23D and 23E, which are fixed with the fastener 35.
    [0056] In this case, the electromagnetic shielding film 27 is interposed between the window panels 23D and 23E, and has its outer perimeter part connected to a conductive film (connection film) 52. This connection film 52 is provided to the along the outer perimeter portion of the window portion 21, that is, an outer perimeter surface of the window panel 23D, and is electrically grounded (by gluing) to the outer retainer 22 with troughs 52a provided in a plurality of locations in the circumferential direction .
    [0057] Even in this structure, the interstice between the electromagnetic shielding film 27 and the external retainer 22 can be filled with the conductive film 52, and therefore an effect similar to that shown in figure 2 and figure 4 described above can be obtained.
    [0058] Note that in the modality described above, the number of window panels that configure the window part 21, the lamination structure, and materials, can be changed, when appropriate. In addition, the layer on which the electromagnetic shielding film 27 is provided may be a different layer from the layer described above. Also in this case, the interstice between the electromagnetic shielding film 27 and the external retainer 22 can be filled with conductive films 41 and 52.
    [0059] In addition, the structure described in the above modality can be selected or can be modified, when appropriate, to another structure without departing from the spirit of the present invention. List of Reference Signs 10 ... Aircraft, 11 ... Cladding, 12 ... Aperture, 13 ... Stringer member, 14 ... Fixing member, 20 ... Cockpit window, 21 ... Window part, 22 External retainer, 23A to 23E ... Window panel, 24A, 24B ... Resin film, 25 ... Heater layer, 27 ... electromagnetic shielding film, 28A, 28B ... Spacer, 31 ... Weatherproof seal, 32 ... Internal retainer, 33 ... Through hole, 34 ... Sleeve, 35 ... Fixer (coupling member), 40 ... Member connection, 41, 52 ... Conductive film (connection film), ..., 41a ... One end, 41b ... Projection part (intermediate part) ,, 41c ... Tip end part , 41d ... Trough (the other end), 50 ... Side window
    权利要求:
    Claims (9)
    [0001]
    1. Cockpit window (20) of an aircraft (10) having an electromagnetic shield, comprising: a plurality of laminated transparent window panels (23A to 23E); an inner retainer on the inner side (32) and an outer retainer on the outer side (22) provided for an outer perimeter part of the window panels (23A to 23E), the retainers (22, 32) interposing the window panels (23A to 23E) and made of a conductive material; a coupling member (35) coupling the inner retainer (32) and the outer retainer (22) to each other; a weather seal (31) provided between the external retainer (22) and the window panels (23A to 23E); an electromagnetic shielding film (27) provided between two of the window panels (23A to 23E) which are opposite each other and made of a conductive material; and a connecting film (41, 52) made of a conductive material and electrically connecting an external perimeter part of the electromagnetic shielding film (27) and the external retainer (22), characterized by the fact that it also comprises: a layer of heater (25) for antifreeze or defogging which is separated from the electromagnetic shielding film (27) is further provided between the plurality of window panels (23A to 23E).
    [0002]
    2. Aircraft cockpit window according to claim 1, characterized by the fact that the electromagnetic shielding film is provided on one side of the internal perimeter from a portion fixed by the internal retainer and the external retainer and the film connection points are inserted into the portion.
    [0003]
    Aircraft cockpit window according to claim 1, characterized by the fact that a plurality of window panels (23A to 23E) comprises glass.
    [0004]
    4. Aircraft cockpit window according to claim 1, characterized by the fact that the connecting film (41, 52) directly contacts the external retainer (22).
    [0005]
    5. Aircraft cockpit window according to claim 1, characterized by the fact that the connecting film (41, 52) is grounded to the external retainer (22) around an entire perimeter of the plurality of window panels (23A to 23E).
    [0006]
    6. Aircraft cockpit window according to claim 1, characterized by the fact that there is no air gap between the plurality of window panels (23A to 23E).
    [0007]
    7. Cockpit window (20) of an aircraft (10) having an electromagnetic shield, comprising: a plurality of transparent laminated window panels (23A to 23E); an inner retainer on the inner side (32) and an outer retainer on the outer side (22) provided for an outer perimeter part of the window panels (23A to 23E), the retainers (22, 32) interposing the window panels (23A to 23E) and made of a conductive material; a coupling member (35) coupling the inner retainer (32) and the outer retainer (22) to each other; a weather seal (31) provided between the external retainer (22) and the window panels (23A to 23E); an electromagnetic shielding film (27) provided between two of the window panels (23A to 23E) which are opposite each other and made of a conductive material; and a connecting film (41, 52) made of a conductive material and electrically connecting an external perimeter part of the electromagnetic shielding film (27) and the external retainer (22), characterized by the fact that the connecting film (52 ) has an end interposed between two of the window panels (23A, 23B) that are opposite each other, to be electrically connected to the electromagnetic shielding film (27), and has another end connected to the external retainer (22) outside the protection panels. window, and an intermediate part between one end and the other end is along an outer perimeter surface of the window panels and is provided so as to fill a space between the outer perimeter part of the electromagnetic shielding film (27) and the external retainer (22).
    [0008]
    8. Aircraft cockpit window according to claim 7, characterized by the fact that the connecting film (41, 52) and the electromagnetic shielding film (27) are connected via a connecting member in the form of a strap (40), provided to surround the outer perimeter part of the electromagnetic shielding film (27), the connecting member (40) being made of a conductive material.
    [0009]
    9. Aircraft characterized by the fact that it comprises the cockpit window having the electromagnetic shielding as defined in any one of claims 1 to 8.
    类似技术:
    公开号 | 公开日 | 专利标题
    BR112012005536B1|2021-01-19|cockpit window of an aircraft having electromagnetic shielding, and aircraft
    KR102276380B1|2021-07-13|Foldable display device
    JP2013060136A|2013-04-04|Window of aircraft, closing member for opening and gasket seal
    JP5931447B2|2016-06-08|Aircraft window, aircraft, aircraft window assembly method.
    JP2011225076A5|2013-01-24|
    CA2678099A1|2008-08-28|Aircraft window member, method of manufacturing the same, and aircraft window assembly
    JP6685350B2|2020-04-22|Aircraft Transparency with Pressure Seal and / or Antistatic Drain
    US20210333913A1|2021-10-28|Touch control display panel and display device
    JP6190216B2|2017-08-30|Aircraft windows and opening closure members
    JP2011158772A|2011-08-18|Display device
    BRPI1001963A2|2012-03-06|ELECTRONIC FLYING BAG COMPUTER TO PROVIDE FLIGHT DATA TO AIRCRAFT PILOTS AND FAN MODULE FOR AN ELECTRONIC FLYING BAG COMPUTER TO PROVIDE FLIGHT DATA TO AIRCRAFT PILOTS
    ES2738276T3|2020-01-21|Aircraft window with electromagnetic shielding and enabled for infrared light
    JP2016533934A|2016-11-04|Glass panels for spacecraft
    US20140097018A1|2014-04-10|Electromagnetic shielded aircraft passenger window
    JP3194294U|2014-11-13|Display device
    KR20200068134A|2020-06-15|Display device
    CN113284419A|2021-08-20|Display panel, display device and vehicle-mounted display device
    BR112021003725A2|2021-05-25|anti-frosted glazing that has a different heating power throughout its surface
    US20160229515A1|2016-08-11|Windshield of aircraft
    KR20150145143A|2015-12-29|Display apparatus
    CN103050062A|2013-04-17|Anti-fog radiation-proof display and processing method thereof
    BR112012030431A2|2021-03-23|rear cover assembly for a device that has ambient light source to emit ambient light to a surface behind the device and display device that has ambient light capabilities
    同族专利:
    公开号 | 公开日
    EP2562078A1|2013-02-27|
    CN102574572A|2012-07-11|
    RU2012110055A|2013-09-20|
    CA2769734A1|2011-10-27|
    JP2011225076A|2011-11-10|
    US8714487B2|2014-05-06|
    CN102574572B|2015-09-23|
    WO2011132349A1|2011-10-27|
    CA2769734C|2014-04-22|
    RU2502632C2|2013-12-27|
    JP5492647B2|2014-05-14|
    EP2562078A4|2014-09-24|
    EP2562078B1|2015-10-21|
    US20130026296A1|2013-01-31|
    BR112012005536A2|2020-08-04|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB1406441A|1972-03-13|1975-09-17|Triplex Safety Glass Co|Laminated transparent assemblies|
    US5139850A|1987-02-03|1992-08-18|Pilkington Plc|Electromagnetic shielding panel|
    GB8713437D0|1987-06-09|1987-07-15|Pilkington Brothers Plc|Shielding panel|
    US4932608A|1987-12-28|1990-06-12|Ppg Industries, Inc.|Aircraft windshield design and method of use|
    US4933227A|1988-12-30|1990-06-12|Ppg Industries, Inc.|Aircraft windshield|
    GB8918859D0|1989-08-18|1989-09-27|Pilkington Plc|Electromagnetic shielding panel|
    JPH1184041A|1997-09-12|1999-03-26|Bridgestone Corp|Light transmission window material with electromagnetic wave shielding property|
    JPH1197878A|1997-09-19|1999-04-09|Bridgestone Corp|Electromagnetic wave shielding light-transmitting window material|
    JP2000286591A|1999-03-30|2000-10-13|Asahi Glass Co Ltd|Electromagnetic shielding window glass|
    FR2793106B1|1999-04-28|2001-06-22|Saint Gobain Vitrage|MULTIPLE INSULATING WINDOWS, ESPECIALLY AIRPLANE WINDOWS, WITH ELECTROMAGNETIC SHIELDING|
    JP4201458B2|2000-03-31|2008-12-24|パナソニック株式会社|Electromagnetic shielding method, electromagnetic shielding window, and electronic circuit board processing machine equipped with electromagnetic shielding window|
    US6561460B2|2000-08-03|2003-05-13|Ppg Industries Ohio, Inc.|Switchable electrochromic devices for use in aircraft transparency windows|
    US20040229607A1|2003-05-12|2004-11-18|La Chapelle Michael De|Wireless communication inside shielded envelope|
    US7143979B2|2003-05-30|2006-12-05|The Boeing Company|Vehicle windshield|
    US7913385B2|2005-12-02|2011-03-29|The Boeing Company|Method of attenuating electromagnetic energy|
    JP4969268B2|2007-02-19|2012-07-04|三菱重工業株式会社|Aircraft window material and method of manufacturing the same|
    RU80143U1|2008-10-15|2009-01-27|Мирослав Петров Маринов|MULTILAYER ELECTRIC HEATED WINDSHIELD|JP5060647B1|2011-09-14|2012-10-31|三菱航空機株式会社|Aircraft windows, opening closures, gasket seals|
    US9221533B1|2011-10-24|2015-12-29|The Boeing Company|Removable window system for space vehicles|
    JP5931447B2|2012-01-11|2016-06-08|三菱航空機株式会社|Aircraft window, aircraft, aircraft window assembly method.|
    CN102730989B|2012-07-03|2014-12-03|北京航空航天大学|Preparation method of organic electrically-heated invisible interlayer glass|
    US9085349B2|2012-10-10|2015-07-21|The Boeing Company|Infrared light enabled and electromagnetic shielding aircraft window|
    US20140097018A1|2012-10-10|2014-04-10|The Boeing Company|Electromagnetic shielded aircraft passenger window|
    JP6030494B2|2013-04-19|2016-11-24|大成建設株式会社|Electromagnetic shielding film mounting tool for electromagnetic shielding window, electromagnetic shielding window using the same, and construction method of electromagnetic shielding window|
    US9073620B2|2013-06-07|2015-07-07|Honda Patents & Technologies North America, Llc|Fastening device for window|
    ITPD20130318A1|2013-11-21|2015-05-22|Isoclima Spa|WINDSHIELD STRUCTURE, PARTICULARLY FOR HELICOPTERS|
    US9745046B2|2014-01-30|2017-08-29|Ppg Industries Ohio, Inc.|Aircraft transparency with pressure seal and/or anti-static drain|
    JP2016132341A|2015-01-19|2016-07-25|三菱航空機株式会社|Aircraft and transport machine|
    JP2016132340A|2015-01-19|2016-07-25|三菱航空機株式会社|Aircraft and transport machine|
    JP2016141362A|2015-02-05|2016-08-08|三菱航空機株式会社|Windshield of aircraft|
    JP6549855B2|2015-02-17|2019-07-24|三菱航空機株式会社|Aircraft windshield|
    US10023289B2|2015-03-10|2018-07-17|Bell Helicopter Textron Inc.|Variable-thickness windshield|
    KR101681558B1|2015-11-09|2016-12-12|국방과학연구소|Radome coupling member for lihgtning and assembly thereof|
    US10293915B2|2016-12-13|2019-05-21|The Boeing Company|Apparatuses and methods for aerodynamic window assemblies|
    FR3068858B1|2017-07-06|2021-04-02|Saint Gobain|ELECTROSTATIC DISCHARGE NOISE SUPPRESSION BY EARLY DISCHARGE OF A STEEL ELEMENT|
    FR3068857B1|2017-07-06|2021-10-29|Saint Gobain|SUPPRESSION OF ELECTROSTATIC DISCHARGE NOISE BY CONDUCTION BETWEEN A STEEL ELEMENT AND THE GLASS PRESS|
    FR3068856B1|2017-07-06|2021-10-29|Saint Gobain|SUPPRESSION OF ELECTROSTATIC DISCHARGE NOISE BY CONDUCTION BETWEEN A STEEL METAL ELEMENT AND THE ELECTRICAL NETWORK OF A GLASS|
    FR3089148B1|2018-12-04|2020-12-11|Saint Gobain|LAMINATED GLAZING WITH PERIPHERAL GRADINAL ELEMENT IN POLYMERIC MATERIAL HAVING MAXIMUM REQUIRED WATER VAPOR PERMEABILITY|
    FR3096957A1|2019-06-04|2020-12-11|Airbus Operations|Aircraft windshield assembly comprising a peripheral frame surrounding a set of panes separated by non-structural uprights with respect to the peripheral frame|
    FR3111632A1|2020-06-22|2021-12-24|Saint-Gobain Glass France|Glazing mounted on a structure with the interposition of a stiffening element with a bearing surface located between the glazing and the structure|
    法律状态:
    2020-08-18| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2020-08-25| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2020-12-08| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2021-01-19| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 24/01/2011, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    JP2010095810A|JP5492647B2|2010-04-19|2010-04-19|Aircraft cockpit window with electromagnetic shield, aircraft|
    JP2010-095810|2010-04-19|
    PCT/JP2011/000365|WO2011132349A1|2010-04-19|2011-01-24|Aircraft cockpit window having electromagnetic shield, and aircraft|
    [返回顶部]