WO2017047281A1 - Film fonctionnel pour hublot d'avion, structure de hublot d'avion et procédé permettant de fonctionnaliser un hublot d'avion - Google Patents

Film fonctionnel pour hublot d'avion, structure de hublot d'avion et procédé permettant de fonctionnaliser un hublot d'avion Download PDF

Info

Publication number
WO2017047281A1
WO2017047281A1 PCT/JP2016/073359 JP2016073359W WO2017047281A1 WO 2017047281 A1 WO2017047281 A1 WO 2017047281A1 JP 2016073359 W JP2016073359 W JP 2016073359W WO 2017047281 A1 WO2017047281 A1 WO 2017047281A1
Authority
WO
WIPO (PCT)
Prior art keywords
window
aircraft
functional film
functional
film
Prior art date
Application number
PCT/JP2016/073359
Other languages
English (en)
Japanese (ja)
Inventor
集 佐々木
啓太 峯
福島　優
大森　裕
Original Assignee
日東電工株式会社
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 日東電工株式会社 filed Critical 日東電工株式会社
Publication of WO2017047281A1 publication Critical patent/WO2017047281A1/fr

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B9/00—Layered products comprising a layer of a particular substance not covered by groups B32B11/00 - B32B29/00
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09J—ADHESIVES; NON-MECHANICAL ASPECTS OF ADHESIVE PROCESSES IN GENERAL; ADHESIVE PROCESSES NOT PROVIDED FOR ELSEWHERE; USE OF MATERIALS AS ADHESIVES
    • C09J201/00—Adhesives based on unspecified macromolecular compounds

Definitions

  • the present invention relates to an aircraft window functional film for imparting functions such as electromagnetic shielding properties, heat shielding properties, and heat insulation properties to aircraft windows. Furthermore, this invention relates to an aircraft window structure provided with the said functional film.
  • a window provided in an aircraft cockpit or cabin is configured by fitting a plate-like transparent window material made of glass or transparent resin into a frame.
  • Aircraft windows allow passengers and crew to see outside the aircraft by capturing visible light from outside the aircraft.
  • the window serves as a heat inlet.
  • the temperature inside the aircraft rises.
  • the window also serves as a heat outlet, the temperature inside the machine is lowered by the heat inside the machine being radiated to the outside.
  • the inflow and outflow of heat through an aircraft window causes an increase in the load on the air conditioner.
  • a solar control coating having a metal layer and a dielectric layer is provided on a window material via a siloxane-based adhesive layer, and a top coat including a polysiloxane material and an overcoat including silicon oxycarbide are provided thereon.
  • a method of providing thermal insulation to an aircraft window material by providing the aircraft window material is disclosed.
  • Aircraft windows serve as entrances and exits for electromagnetic waves (submillimeter to long wave) in addition to entrances and exits for visible light and heat. Since equipment used for aircraft navigation is strongly affected by electromagnetic waves, if electromagnetic waves inside the aircraft leak out of the aircraft, navigation may be adversely affected. For this reason, it is difficult to wirelessly control lighting devices, electronic devices, etc. in an aircraft, which is a factor that complicates the wiring of in-flight facilities. In addition, in order to ensure navigation safety, the use of wireless devices such as mobile phones on board is restricted. In order to enable wireless use in the aircraft, it is necessary to provide electromagnetic shielding to the aircraft windows to prevent leakage of electromagnetic waves inside the aircraft and leakage of electromagnetic waves outside the aircraft into the aircraft. is there.
  • Patent Document 2 discloses an aircraft window material having electromagnetic shielding properties, in which an acrylic window material and a metal mesh are laminated and integrated.
  • a resin film provided with a metal mesh on the surface is disposed on an acrylic window material via a thermosetting adhesive such as urethane, and the adhesive is obtained by heat treatment in an autoclave.
  • the window material and the metal mesh are laminated and integrated by curing.
  • Patent Document 3 discloses a method of imparting electromagnetic wave shielding properties to an aircraft window by bonding a transparent film having a conductive thin film to the inner surface of one of the laminated windows of the aircraft window.
  • Patent Documents 1 to 3 are specialized for either heat shielding or electromagnetic wave shielding, and have heat shielding properties and electromagnetic wave shielding properties while maintaining visible light permeability. It is difficult to achieve both.
  • conventional aircraft window materials require heat curing or light curing of an adhesive when a metal mesh or a conductive layer is laminated and integrated on a glass plate or a resin plate constituting the window material. Therefore, these functional window materials are generally used as window materials for new aircraft. In order to impart heat shielding properties and electromagnetic wave shielding properties to existing aircraft, it is necessary to remove window materials from the aircraft and replace them with these window materials. Generally, since the window material of an aircraft is attached to the frame body through an airtight seal material (see FIG. 2B), replacement of the window material requires enormous work and cost.
  • an object of the present invention is to provide an aircraft window functional film that has transparency of visible light, heat shielding properties, and electromagnetic wave shielding properties, and can be easily applied to existing aircraft.
  • the functional film of the present invention includes a functional thin film and a transparent protective layer in this order on the first main surface of the transparent film substrate.
  • the transparent protective layer is the outermost surface layer of the functional film.
  • an adhesive layer for bonding with an aircraft window material may be provided on the second main surface of the transparent film base material.
  • the functional thin film is composed of a laminate of a metal oxide layer and a metal layer, and preferably has a metal layer between two metal oxide layers.
  • a metal layer what contains 90 weight% or more of silver is preferable.
  • the transparent protective layer is preferably provided in contact with the functional thin film.
  • a resin mainly composed of an acrylic resin is preferably used as a material for the transparent protective layer.
  • the transparent protective layer has a thickness of 30 nm to 1000 nm.
  • the aircraft window structure according to the present invention includes a window material made of glass or transparent resin, and the functional film.
  • a window material made of glass or transparent resin
  • the functional film By applying the functional film described above to an aircraft window structure, functions such as electromagnetic wave shielding properties, heat shielding properties, and heat insulating properties can be imparted to aircraft windows.
  • the functional film of the present invention includes a functional thin film made of a laminate of metal and metal oxide, it has a high visible light transmittance and an excellent shielding property against electromagnetic waves and heat.
  • the transparent protective layer is provided on the outermost surface of the functional film, the functional thin film is hardly scratched or peeled off even when it is manually attached to an aircraft window material or attached to a frame. Therefore, the functional film of the present invention can be easily applied to existing aircraft windows.
  • A is a schematic perspective view of an aircraft window frame
  • B is a cross-sectional view taken along line B1-B2.
  • FIG. 1 is a schematic cross-sectional view showing a configuration example of an aircraft window functional film.
  • the functional film 100 includes a functional thin film 20 and a transparent protective layer 30 in this order on one main surface of the transparent film substrate 10.
  • an adhesive layer 40 is provided on the other main surface of the transparent film substrate 10.
  • a flexible resin film having a visible light transmittance of 80% or more is preferably used as the transparent film substrate 10.
  • the visible light transmittance is measured according to JIS A5759: 2008 (film for architectural window glass).
  • the thickness of the transparent film substrate 10 is not particularly limited, but is about 10 ⁇ m to 300 ⁇ m, for example.
  • the resin material constituting the transparent film substrate is preferably excellent in heat resistance. Examples of the resin material constituting the transparent film substrate include polyethylene terephthalate (PET), polyethylene naphthalate (PEN), polyether ether ketone (PEEK), polycarbonate (PC), and cyclic polyolefin.
  • a hard coat layer or the like may be provided on one or both main surfaces of the transparent film substrate 10.
  • Surface modification treatment such as treatment may be performed.
  • the functional thin film 20 provided on the first main surface of the transparent film substrate 10 transmits visible light and shields infrared rays and electromagnetic waves (submillimeter wave to long wave radio waves).
  • a functional thin film consists of a laminated body of a metal layer and a metal oxide layer.
  • the metal layer has electromagnetic wave shielding properties.
  • the metal layer reflects infrared rays, in addition to electromagnetic wave shielding properties, the metal layer exhibits heat shielding properties by reducing inflow of near infrared rays from outside the machine.
  • the metal oxide layer controls the wavelength selectivity of transmission and reflection, and has an effect of achieving both high visible light transmittance and infrared reflectance.
  • the metal oxide layer can function as a protective layer for preventing deterioration of the metal layer.
  • the functional thin film 20 preferably has a configuration in which the metal layer 25 is sandwiched between the metal oxide layers 21 and 22, as shown in FIG. By alternately laminating metal layers and metal oxide layers, the wavelength selectivity of transmission and reflection is enhanced.
  • the functional thin film 20 may be composed of three layers of the metal oxide layer 21 / the metal layer 25 / the metal oxide layer 22, and may include other layers. For example, for the purpose of improving the adhesion between the metal layer 25 and the metal oxide layers 21 and 22 and imparting durability to the metal layer, there are other metal layers or metal oxide layers between them. You may do it. Further, by increasing the number of alternating layers of metal layers and metal oxide layers to form a 5-layer structure, a 7-layer structure, etc., the wavelength selectivity of transmission and reflection of visible light and near-infrared light can be further improved. .
  • the metal constituting the metal layer silver, gold, copper and alloys thereof are preferably used because they have both electromagnetic shielding properties and infrared reflectivity. Among these, silver or a silver alloy is preferable in order to achieve both high visible light transmittance and infrared reflectance.
  • the metal layer 25 preferably has a silver content of 90% by weight or more. When the metal layer 25 is a silver alloy containing a metal other than silver, Cu, Au, Pd, Bi, Ge, Ga, Ti, Ni, Sn are used as the metal other than silver from the viewpoint of imparting high durability to silver. Etc. are preferably used.
  • the metal oxide layers 21 and 22 are preferably amorphous films.
  • An amorphous metal oxide has a higher film density than a crystalline film and is excellent in moisture and gas barrier properties.
  • a metal oxide having a refractive index of 1.5 or more is preferably used as the material of the metal oxide layers 21 and 22.
  • the material having the above refractive index include oxides of metals such as Ti, Zr, Hf, Nb, Zn, Al, Ga, In, Tl, Sn, Mo, Ta, and W, or composite oxides of these metals. Is mentioned.
  • the metal oxide material is preferably an oxide of one or more metals selected from the group consisting of Sn, In, Zn, Ti, and Nb.
  • the composite metal oxide containing a zinc oxide and a tin oxide is used. Since metal oxides containing zinc oxide and tin oxide are excellent in chemical stability (durability against acids, alkalis, chloride ions, etc.), they have a high effect of suppressing deterioration of the metal layer.
  • metal oxide containing zinc oxide and tin oxide in addition to zinc stannate (ZTO), zinc oxide and tin oxide, metals such as In, Al, and Ga, or those containing these oxides are preferably used.
  • the thicknesses of the metal layer 25 and the metal oxide layers 21 and 22 are appropriately set in consideration of the refractive index of the material so that the functional thin film 20 transmits visible light and selectively reflects near infrared light. Is done.
  • the thickness of the metal layer 25 can be adjusted, for example, in the range of 5 nm to 50 nm, preferably 7 nm to 25 nm, more preferably 10 nm to 20 nm.
  • the thickness of the metal oxide layers 21 and 22 can be adjusted, for example, in the range of 3 nm to 80 nm, preferably 3 nm to 50 nm, more preferably 3 nm to 35 nm.
  • the method for forming the metal layer and the metal oxide layer is not particularly limited, but film formation by a dry process such as sputtering, vacuum evaporation, CVD, or electron beam evaporation is preferable.
  • Transparent protective layer By providing the transparent protective layer 30 on the functional thin film 20, the functional thin film can be prevented from being scratched or deteriorated. Moreover, by providing the transparent protective layer, it is possible to prevent the functional thin film from being scratched or peeled off during operations such as laminating a functional film to an aircraft window material. In order to enhance the protection of the functional thin film, the transparent protective layer 30 is preferably provided in contact with the functional thin film 20.
  • the transparent protective layer 30 preferably has a high visible light transmittance and is excellent in mechanical strength and chemical strength.
  • a functional film When a functional film is bonded to a window material, the film may be once rounded into a cylindrical shape for alignment or the like.
  • an organic cured resin is preferably used as the material of the transparent protective layer because cracks and the like are less likely to occur.
  • the organic substance include actinic ray curable or thermosetting materials such as fluorine, acrylic, urethane, ester, and epoxy, and organic / inorganic hybrid materials in which an organic component and an inorganic component are chemically bonded.
  • the cured resin layer which has acrylic resin as a main component is preferable.
  • the cured resin for the transparent protective layer preferably has a crosslinked structure.
  • a crosslinked structure derived from a compound (crosslinking agent) having an acidic functional group and a polymerizable functional group in the same molecule.
  • Examples of the acidic functional group in the cross-linking agent include a carboxy group, a sulfonic acid group, and a phosphoric acid group.
  • Examples of the polymerizable functional group in the crosslinking agent include an ethylenically unsaturated group, a silanol group, and an epoxy group. Among these, an ethylenically unsaturated group is preferable, and a (meth) acryloyl group is particularly preferable.
  • an ester compound having an acidic group and a polymerizable functional group in the same molecule is preferably used as a crosslinking agent.
  • examples of such compounds include esters of polyvalent acids such as phosphoric acid, sulfuric acid, oxalic acid, succinic acid, phthalic acid, fumaric acid and maleic acid.
  • the said ester compound may be polyvalent esters, such as a diester and a triester, it is preferable that at least 1 in the acidic group of a polyvalent acid is not esterified.
  • an ester compound (phosphate ester compound) of phosphoric acid and an organic acid having a polymerizable functional group is preferable in terms of enhancing the adhesion between the transparent protective layer and the functional thin film.
  • the improvement in the adhesion between the transparent protective layer and the metal oxide layer is that the acidic group in the ester compound has a high affinity with the metal oxide, and in particular, the phosphate hydroxy group in the phosphate ester compound is in contact with the metal oxide layer. It is presumed to be derived from the excellent affinity of.
  • the content of the crosslinking agent in the resin composition when forming the transparent protective layer is preferably 1% by weight to 40% by weight, more preferably 1.5% by weight to 35% by weight, and further 2% by weight to 20% by weight. preferable. If the content of the crosslinking agent is excessively small, the effect of improving strength and adhesion may not be sufficiently obtained. On the other hand, if the content of the cross-linking agent is excessively large, the curing rate at the time of forming the transparent protective layer may be reduced and the hardness may be reduced, or the sliding property of the transparent protective layer surface may be reduced and the scratch resistance may be reduced. is there.
  • the method for forming the transparent protective layer 30 is not particularly limited.
  • the transparent protective layer is prepared by, for example, dissolving the organic material, or a curable monomer or oligomer of the organic material, and the ester compound in a solvent to prepare a solution, coating the solution on the functional thin film 20, and removing the solvent. After drying, it is preferably formed by a method of curing by irradiation with ultraviolet rays, electron beams or the like or application of thermal energy.
  • the transparent protective layer 30 is made of a coupling agent such as a silane coupling agent or a titanium coupling agent, a leveling agent, an ultraviolet absorber, an antioxidant, or a heat stabilizer.
  • a coupling agent such as a silane coupling agent or a titanium coupling agent
  • a leveling agent such as a silane coupling agent or a titanium coupling agent
  • an ultraviolet absorber such as an antioxidant
  • a heat stabilizer such as lubricants, plasticizers, anti-coloring agents, flame retardants and antistatic agents may be included. The content of these additives can be appropriately adjusted within a range not impairing the object of the present invention.
  • the transparent protective layer 30 has low visible light absorption in addition to having high visible light transmittance. If far-infrared absorption by the transparent protective layer is small, far-infrared light in the machine passes through the transparent protective layer and reaches the functional thin film 20 and is reflected by the metal layer 25 to the inside of the machine. Therefore, there is little heat radiation outside the machine due to heat conduction from the window (the heat reflux rate is small), and the heat insulation inside the machine is enhanced.
  • the thickness of the transparent protective layer 30 is preferably 1000 nm or less, more preferably 500 nm or less, and even more preferably 300 nm or less.
  • the optical thickness (product of refractive index and thickness) of the transparent protective layer suppresses the iris phenomenon (a phenomenon in which the reflected light is colored in a rainbow pattern) due to overlap with the visible light wavelength, and the visibility is good
  • the thickness of the transparent protective layer 30 is preferably 150 nm or less, more preferably 130 nm or less, still more preferably 110 nm or less, and particularly preferably 100 nm or less.
  • the thickness of the transparent protective layer is preferably 30 nm or more, more preferably 40 nm or more, and further preferably 50 nm or more.
  • An adhesive layer 40 for bonding the functional film and the window material of the aircraft may be provided on the second main surface (the surface where the functional thin film is not formed) of the transparent film substrate 10.
  • the adhesive constituting the adhesive layer 40 preferably has a high visible light transmittance and a small refractive index difference from the transparent film substrate 10. Since curing is not required at the time of bonding, an adhesive (pressure sensitive adhesive) is preferable as the adhesive.
  • the acrylic pressure-sensitive adhesive is excellent in optical transparency, exhibits appropriate wettability, cohesiveness, and adhesiveness, and is excellent in weather resistance, heat resistance, etc., so an adhesive layer attached to a transparent film substrate It is suitable as a material.
  • the adhesive layer 40 preferably has a low ultraviolet transmittance.
  • the layer 40 By reducing the ultraviolet transmittance of the adhesive layer 40, it is possible to suppress the deterioration of the film substrate and the functional thin film caused by ultraviolet rays such as sunlight.
  • the layer preferably contains an ultraviolet absorber in the adhesive.
  • deterioration of the functional thin film resulting from ultraviolet rays from the outdoors can also be suppressed by using a transparent film substrate containing an ultraviolet absorber.
  • the exposed surface of the adhesive layer 40 is preferably covered with a protective film (not shown) for the purpose of preventing contamination of the exposed surface until the functional film is put to practical use.
  • the functional film of the present invention has a visible light transmittance of preferably 60% or more, and more preferably 65% or more.
  • the shielding coefficient of the functional film is preferably 0.70 or less, and more preferably 0.60 or less.
  • the modified emissivity of the functional film measured from the transparent protective layer 30 side is preferably 0.20 or less, more preferably 0.18 or less, and further preferably 0.16 or less.
  • the corrected emissivity is measured according to JlS R3107: 1998 (calculation method of thermal resistance of plate glass and heat transmissivity in architecture).
  • the electromagnetic wave shielding performance of the functional film according to the KEC (Kansai Electronics Industry Promotion Center) method is preferably 20 dB or more, and more preferably 30 dB or more. As described above, these characteristics are achieved by appropriately selecting the material of each layer constituting the functional film.
  • FIG. 2 shows an example of an aircraft window structure.
  • 2A is a schematic perspective view of an aircraft window frame
  • FIG. 2B is a cross-sectional view taken along line B1-B2.
  • the window material is a transparent member made of a transparent resin material such as acrylic or polycarbonate or glass.
  • a planar window material is illustrated in FIG. 2B, the window material may be curved.
  • the outer peripheral edge of the outer panel 51 and the central panel 53 is attached to the frame body 57 via a sealing material 58.
  • a space 68 between the outer panel 51 and the central panel 53 has an anti-fogging role.
  • the outer panel 51 supports the pressurization in the machine. If the outer panel 51 is broken, the central panel 53 can support the pressurization.
  • the inner panel 55 is thinner than the outer panel and the central panel and cannot support the pressurization, but restricts access to the central panel from the inside of the aircraft to protect the central panel and reduce noise in the aircraft. Is provided.
  • the inner panel 55 is detachably attached to the frame body 57.
  • the aircraft window can be functionalized by applying the functional film of the present invention to the aircraft window structure.
  • Functionalization means imparting functions such as electromagnetic wave shielding properties, heat shielding properties, and heat insulating properties.
  • a method of applying a functional film to an aircraft window structure a method of fixing the film to the frame 57 and arranging the film in spaces 68 and 69 formed between the window members, and the window member 51. , 53, 55, and a method of attaching a film to the main surface.
  • the film When disposing a film in the space, the film may be fixed to the inner peripheries 69A and 69B of the frame 57, and the film is applied to the inner peripheries 68A and 68B of the sealing material 58 provided on the inner periphery of the frame 57. It may be fixed.
  • the window members 51, 53, and 55 When the film is bonded to the window members 51, 53, and 55, the window members 51, 53, and 55 may be bonded to any of the main surfaces 61, 63, and 65 on the outside of the machine and the main surfaces 62, 64, and 66 on the inside of the machine.
  • the functional film 100 can achieve both the transparency of visible light and the heat shielding property by near-infrared reflection, and can impart an electromagnetic wave shielding property to the window structure.
  • electromagnetic wave shielding can be more reliably performed.
  • the sealing material 58 is insulative, electromagnetic waves may leak from the sealing material portion in the gap between the functional film and the frame 57.
  • electromagnetic waves may leak from the gap.
  • a conductive member may be attached to the outer peripheral edge of the window material or the frame.
  • the conductive member include a metal foil, a metal strip, a metal lattice, a conductive film having a metal layer on the film surface, and a conductive tape. Since these conductive members are provided on the outer periphery of the window material, the visibility is not greatly affected. Therefore, the conductive member provided for the purpose of preventing leakage of electromagnetic waves from the gap does not have to be transparent.
  • the method of applying the functional film to the aircraft window structure is preferably a method of bonding the film to the main surface of the window material.
  • the adhesive layer 40 is attached to the functional film 100 in advance, the window material and the film may be bonded together via the adhesive layer 40.
  • the films are bonded to the facing surfaces 62 and 63 of these window materials.
  • the functional film is bonded to a surface other than the opposed surfaces 62 and 63 of the sealed window material.
  • the functional film is bonded to either the machine inner main surface 64 of the central panel 53 and both the main surfaces 65 and 66 of the inner panel 55.
  • the functional film of the present invention does not require curing of an adhesive or the like when being attached to a window material, the functional film can be bonded to the inboard main surface 64 without removing the central panel 53 from the aircraft window material. it can. Bonding needs to be performed manually, but the functional film 100 is provided with the transparent protective layer 30 on the functional thin film 20, so that the functional thin film is prevented from being scratched or peeled off during the bonding operation. it can.
  • the method for attaching the functional film to the window material via the adhesive layer is not particularly limited.
  • water bonding is preferable.
  • liquid is present between the adhesive and the adherend at the time of bonding, so that the bonding force is low, so that the positioning is easy.
  • water evaporates with time and the adhesive strength is improved, so that it is possible to satisfy bonding workability, suppression of air bubbles and wrinkles, and adhesion after bonding.
  • a functional film is bonded to the main surface of the window material in contact with the cabin.
  • the inner main surface 66 of the inner panel 55 is in contact with the cabin.
  • the transparent protective layer 30 is exposed on the aircraft interior side, and toward the inside of the aircraft, the transparent protective layer 30, the functional thin film. 20, a structure in which the transparent film substrate 10, the adhesive layer 40, and the window material 55 are arranged in this order is formed.
  • the functional film of the present invention can impart heat shielding properties in addition to providing electromagnetic shielding properties and heat shielding properties to aircraft windows.
  • the functional film is applied to the aircraft window structure composed of the three windows of the outer panel, the center panel, and the inner panel has been described.
  • the present invention can also be applied to an aircraft window structure including one or two window members and an aircraft window structure including four or more window members.
  • electromagnetic wave shielding properties and heat shielding properties can be imparted while maintaining the transparency of visible light.
  • heat insulation can be provided by bonding a functional film to the main surface of the window material in contact with the interior of the machine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Organic Chemistry (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)
  • Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
  • Adhesives Or Adhesive Processes (AREA)

Abstract

L'invention concerne un film fonctionnel; et une structure de hublot d'avion. Ce film fonctionnel (100) comprend séquentiellement, sur une première surface principale d'une base de film transparent (10), un film mince fonctionnel (20) qui est composé d'un stratifié de couches d'oxyde métalliques (21, 22) et d'une couche métallique (25), et d'une couche protectrice transparente (30), dans cet ordre. La couche protectrice transparente (30) sert de couche de surface la plus à l'extérieur de ce film fonctionnel (100). Ce film fonctionnel est utilisé, par exemple, dans le but de conférer à une structure de hublot d'avion des fonctions telles que des propriétés de blindage électromagnétique, des propriétés de bouclier thermique et des propriétés d'isolation thermique.
PCT/JP2016/073359 2015-09-17 2016-08-08 Film fonctionnel pour hublot d'avion, structure de hublot d'avion et procédé permettant de fonctionnaliser un hublot d'avion WO2017047281A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2015183983A JP2017056862A (ja) 2015-09-17 2015-09-17 航空機窓用機能性フィルム、航空機窓構造体、および航空機窓の機能化方法
JP2015-183983 2015-09-17

Publications (1)

Publication Number Publication Date
WO2017047281A1 true WO2017047281A1 (fr) 2017-03-23

Family

ID=58288886

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2016/073359 WO2017047281A1 (fr) 2015-09-17 2016-08-08 Film fonctionnel pour hublot d'avion, structure de hublot d'avion et procédé permettant de fonctionnaliser un hublot d'avion

Country Status (2)

Country Link
JP (1) JP2017056862A (fr)
WO (1) WO2017047281A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018180128A1 (fr) * 2017-03-30 2018-10-04 富士フイルム株式会社 Corps stratifié, matériau de construction, substance filtrante, et dispositif de refroidissement par rayonnement
WO2018181220A1 (fr) * 2017-03-31 2018-10-04 日東電工株式会社 Substrat transmettant la lumière pour réfléchir des rayons thermiques, et fenêtre réfléchissant les rayons thermiques
WO2018181219A1 (fr) * 2017-03-31 2018-10-04 日東電工株式会社 Substrat transmettant la lumière permettant de supprimer la transmission de rayons thermiques et unité de substrat transmettant la lumière
JP2018171908A (ja) * 2017-03-31 2018-11-08 日東電工株式会社 熱線透過抑制透光性基材、透光性基材ユニット
JP2018173630A (ja) * 2017-03-31 2018-11-08 日東電工株式会社 熱線反射透光性基材、熱線反射窓
CN110406208A (zh) * 2019-08-12 2019-11-05 中国航空工业集团公司沈阳飞机设计研究所 一种耐热承力构件
CN112505871A (zh) * 2020-11-25 2021-03-16 中国工程物理研究院激光聚变研究中心 一种高空飞行器光学窗口防护装置及使用方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6967954B2 (ja) * 2017-12-05 2021-11-17 東京エレクトロン株式会社 排気装置、処理装置及び排気方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2003211577A (ja) * 2002-01-22 2003-07-29 Toyobo Co Ltd 電磁波シールド性を有する車両
JP2003523911A (ja) * 1999-04-28 2003-08-12 サン−ゴバン グラス フランス 電磁シールドを有する絶縁用多重ガラス、特に航空機の窓
WO2008102737A1 (fr) * 2007-02-19 2008-08-28 Mitsubishi Heavy Industries, Ltd. Élément de hublot d'avion, son procédé de fabrication et élément de hublot d'avion
JP2013521160A (ja) * 2010-03-01 2013-06-10 シーピーフィルムズ， インク． 低放射ｅｍｉ遮蔽窓フィルム

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2003523911A (ja) * 1999-04-28 2003-08-12 サン−ゴバン グラス フランス 電磁シールドを有する絶縁用多重ガラス、特に航空機の窓
JP2003211577A (ja) * 2002-01-22 2003-07-29 Toyobo Co Ltd 電磁波シールド性を有する車両
WO2008102737A1 (fr) * 2007-02-19 2008-08-28 Mitsubishi Heavy Industries, Ltd. Élément de hublot d'avion, son procédé de fabrication et élément de hublot d'avion
JP2013521160A (ja) * 2010-03-01 2013-06-10 シーピーフィルムズ， インク． 低放射ｅｍｉ遮蔽窓フィルム

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018180128A1 (fr) * 2017-03-30 2018-10-04 富士フイルム株式会社 Corps stratifié, matériau de construction, substance filtrante, et dispositif de refroidissement par rayonnement
JPWO2018180128A1 (ja) * 2017-03-30 2020-06-11 富士フイルム株式会社 積層体、建材、窓材及び放射冷却装置
US10766225B2 (en) 2017-03-30 2020-09-08 Fujifilm Corporation Laminate, building material, window material, and radiation cooling device
WO2018181220A1 (fr) * 2017-03-31 2018-10-04 日東電工株式会社 Substrat transmettant la lumière pour réfléchir des rayons thermiques, et fenêtre réfléchissant les rayons thermiques
WO2018181219A1 (fr) * 2017-03-31 2018-10-04 日東電工株式会社 Substrat transmettant la lumière permettant de supprimer la transmission de rayons thermiques et unité de substrat transmettant la lumière
JP2018171908A (ja) * 2017-03-31 2018-11-08 日東電工株式会社 熱線透過抑制透光性基材、透光性基材ユニット
JP2018173630A (ja) * 2017-03-31 2018-11-08 日東電工株式会社 熱線反射透光性基材、熱線反射窓
EP3605165A4 (fr) * 2017-03-31 2020-12-30 Nitto Denko Corporation Substrat transmettant la lumière permettant de supprimer la transmission de rayons thermiques et unité de substrat transmettant la lumière
US11933997B2 (en) 2017-03-31 2024-03-19 Nitto Denko Corporation Heat-ray-transmission-controllable, light-transmissive base material and light-transmissive base material unit
CN110406208A (zh) * 2019-08-12 2019-11-05 中国航空工业集团公司沈阳飞机设计研究所 一种耐热承力构件
CN110406208B (zh) * 2019-08-12 2022-06-07 中国航空工业集团公司沈阳飞机设计研究所 一种耐热承力构件
CN112505871A (zh) * 2020-11-25 2021-03-16 中国工程物理研究院激光聚变研究中心 一种高空飞行器光学窗口防护装置及使用方法

Also Published As

Publication number Publication date
JP2017056862A (ja) 2017-03-23

Similar Documents

Publication Publication Date Title
WO2017047281A1 (fr) Film fonctionnel pour hublot d'avion, structure de hublot d'avion et procédé permettant de fonctionnaliser un hublot d'avion
US8771444B2 (en) Low emissivity and EMI shielding window films
JP6000991B2 (ja) 赤外線反射フィルム
US8951372B2 (en) Low emissivity and EMI shielding films
WO2015133370A1 (fr) Substrat réfléchissant les infrarouges et procédé pour sa production
JP5959746B2 (ja) 光透過性積層体
WO2016021543A1 (fr) Film réfléchissant les infrarouges
KR102007723B1 (ko) 열차단 필름
JP6370347B2 (ja) 赤外線反射フィルム
JP2018171908A (ja) 熱線透過抑制透光性基材、透光性基材ユニット
JP2017068118A (ja) 赤外線反射フィルム
KR20190128651A (ko) 열선 반사 투광성 기재 및 열선 반사창
WO2018181220A1 (fr) Substrat transmettant la lumière pour réfléchir des rayons thermiques, et fenêtre réfléchissant les rayons thermiques
JP7343117B1 (ja) 遮熱用粘着フィルム
WO2018181219A1 (fr) Substrat transmettant la lumière permettant de supprimer la transmission de rayons thermiques et unité de substrat transmettant la lumière
JP2018171831A (ja) 熱線反射透光性基材、熱線反射窓
JP2017047552A (ja) 光透過性積層体

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 16846154

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 16846154

Country of ref document: EP

Kind code of ref document: A1