Class / Patent application number | Description | Number of patent applications / Date published |
244129300 | Windows | 59 |
20080197237 | Method For Making Window Frame - A method for making a window frame for installation in the exterior shell of an aircraft, which comprises at least one outer flange, an inner flange, and a vertical flange arranged perpendicular to and between these two flanges, contemplates that first a semifinished part comprising multiple, individual substructures is made, which next is inserted into a molding tool, into which, under pressure and temperature, resin is injected, and that the component made in this manner subsequently is hardened in the molding tool. The semifinished part has a layer structure, which comprises a web material, fiber bundles, or a combination of fiber bundles and web material. | 08-21-2008 |
20080217479 | Window installation method and apparatus - An exemplary window frame assembly includes a window frame and spring clips. The window frame includes a window frame body, and flanges extend from the window frame body. The spring clips are removably attachable to the flanges. Each flange may define at least one first locking member and each spring clip may define at least one second locking member configured to engage the first locking member. For example, the at least one first locking member may include saw tooth grooves and the at least one second locking member may include a pair of angled tabs. As another example, the at least one first locking member may include a pair of angled tabs and the at least one second locking member may include saw tooth grooves. Each spring clip may further define a release mechanism, such as a tab, that is configured to disengage the spring clip and the flange. | 09-11-2008 |
20080230653 | Self-Powered Dimmable Windows with Integrated Controls - An electrically controlled dimmable window for aircraft includes a controller and power that eliminates the need for wiring connections to on-board systems. The controller is integrated into the sidewall in which the window is mounted. Power for controlling the window is derived from an energy harvesting device that generates power by converting thermal gradients, motion/vibration or light energy present near the window. The integrated controller includes passenger controls for adjusting the opacity of the window, power conditioning circuitry, an electrical power storage device such as a battery, a processor and a radio receiver. The window can be remotely controlled by a cabin attendant from a central controller that transmits window control signals to the radio receiver. | 09-25-2008 |
20080265096 | Aircraft door window - An airplane door window of a passenger plane, includes an outer pane, an inner pane, an intermediate pane situated parallel between the outer pane and inner pane and designed as an optical lens body for the inspection of impact surfaces for emergency slides, portable staircases or boarding fingers. The outer pane and the inner pane are spaced apart from each other, arranged substantially parallel to each other in a continuous window gasket, and form an intermediate space. The intermediate pane is inserted into a continuous groove of the window gasket, and extends essentially parallel to the outer pane and the inner pane over a partial area of the intermediate space. | 10-30-2008 |
20080308677 | Radio frequency shielding apparatus system and method - A system for shielding an aircraft from electromagnetic energy includes a fuselage, aperture, window mounting, and window plug. The fuselage provides an electrically conductive envelope. The aperture is disposed in the fuselage. The window mounting spans the aperture. The window plug spans the aperture. The window mounting and the window plug are electrically coupled to the fuselage and provide an electrical path spanning the aperture. | 12-18-2008 |
20090014589 | RF Shielding for Aircraft Windows - A window includes a pane and a geometrically patterned grid. The grid is embedded in the pane and the grid comprises an electrically conductive material and is operable to attenuate radio frequency (RF) energy. | 01-15-2009 |
20090084900 | Window element for insertion in a window cutout in an outer skin of an aircraft - A window element for insertion in a window cutout in an outer skin of an aircraft, with a window frame for accommodating a window package and a press-on frame. The window frame can be attached to the inside of the outer skin in the region of the window cutout and can be riveted to the external skin, wherein for attaching the press-on frame at least one press-on frame fitting is connected to the window frame and to the outer skin, in particular is riveted to the window frame and to the outer skin, and the window frame comprises an essentially L-shaped or rectangular cross-sectional geometric shape. | 04-02-2009 |
20090230246 | WINDOW PANEL AND METHOD OF MANUFACTURING SUCH A WINDOW, AIRCRAFT COMPRISING A WINDOW PANEL - This invention relates to the design of aircraft ( | 09-17-2009 |
20090321571 | Window for aircraft with microstructure as a sunscreen - An aircraft window includes a microstructure so that light rays with a correspondingly large angle of incidence are reflected back to the exterior region. By contrast, light rays with another, i.e. smaller, angle of incidence are allowed to pass almost without hindrance. The microstructures are designed as optical prisms, wherein the order of magnitude of the prisms is in the region of light wave lengths. | 12-31-2009 |
20100044513 | AIRCRAFT CABIN WINDOW ASSEMBLY METHOD - A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, the cabin window including an outer transparent element and at least one inner transparent element. A non-through hole is made in a portion of the side wall along the edge of the bay. Subsequently, the outer transparent element is positioned in the bay from the exterior of the fuselage. The element includes a first part which has a diameter greater than that of the bay and which is shaped to co-operate with the above mentioned portion such as to block the outer transparent element in the bay both laterally and longitudinally. A second part of the outer transparent element has a groover that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove. | 02-25-2010 |
20100051747 | LEAKTIGHT FRAME FOR A WINDOW AND A MECHANICAL ASSEMBLY PROVIDED WITH SUCH A FRAME - A leaktight frame ( | 03-04-2010 |
20100108812 | AEROSPACE ARTICLES MADE FROM QUASI-ISOTROPIC CHOPPED PREPREG - Quasi-isotropic chopped prepreg is used to make parts found in aerospace vehicles. Exemplary aerospace parts that are made using quasi-isotropic chopped prepreg include aircraft window frames, wing fairing supports, flange supports, frame gussets, rudder actuator brackets, shear ties, seat pedestals, cargo floor flange supports, storage bin fittings, antenna supports, torque tube pans, handle boxes, side guide fittings, wing box covers and intercostals. | 05-06-2010 |
20100123043 | SOUND INSULATING GLAZING DEVICE, IN PARTICULAR FOR AIRCRAFT AND SOUNDPROOFING METHOD FOR GLAZING - Sound insulating glazing device for aircrafts, ground or maritime transportation vehicles, buildings, or others, including glazing, a sealing joint in a shape and size corresponding to the edge of the glazing and designed for assembly on said edge, sound insulation, made of at least two materials, a first resilient material and a second material with less resilience than the first, the sound insulation being used against the field of said glazing, between the glazing and the sealing joint. The invention is also for aircrafts that are equipped with at least a glazing device and a soundproofing method for glazing. | 05-20-2010 |
20100127126 | WATER-RESIST MEANS FOR AIRCRAFT WINDOWS - The subject matter of the disclosed embodiments is a device for mounting a window glass including a seal covering a peripheral edge of the window glass and provided with a strip bearing against a peripheral flat of a frame of the window. The seal includes a flange engaging in the recess of the window and is provided with a squeegee lip bearing against the edge of the frame. | 05-27-2010 |
20100163675 | TRANSPARENCY HAVING SENSORS - A transparency, e.g. an aircraft laminated windshield, includes one or more sensors to monitor performance of one or more properties, e.g. a heating arrangement of the windshield, and to generate signals representative of the performance of the properties. One part of a connector, external of the transparency and connected to the sensors is connected to a system positioned in the aircraft. The system receives a signal from each of the sensors, and processes the signals to determine difference between performance of the property as indicated by the signal received and a preferred performance of the property to provide real time monitoring of the performance of the windshield. With this arrangement information regarding the performance of the windshield is available to schedule timely repair or replacement of the windshield that is performing outside of acceptable limits. | 07-01-2010 |
20100163676 | AIRCRAFT WITH WINDSHIELD GLASS PLATES INTERCHANGEABLE BETWEEN DIFFERENT TYPES - An aircraft in which it is possible to replace windshield panes of the mineral type with windshield panes of the organic type and vice versa, without the frame of the aircraft structure having to be modified. The pane is held in place on the frame by a window pane retainer specific to the pane. The frame has no through-holes opening to the outside of the aircraft for fastening the pane. The window pane retainer specific to a pane of the organic type has pins passing through the acrylic panes. The disclosed embodiments also relate to a method of replacing a pane of a first type with a pane of a second type. | 07-01-2010 |
20100224729 | Device for installing windshield panes - A fastening device for at least one pair of window panes, especially aircraft windshield window panes, each having a window pane retainer equipped with a frame that is applied to the borders of receptacle openings for the window panes, wherein the frames have a pair of posts facing one another provided with matching profiles that can mate the aforementioned posts, one inside the other, in a fastening line of the window pane retainer on the common border to the openings that receive the pair of panes. | 09-09-2010 |
20100230543 | METHOD OF APPLYING AN ELECTRIC CONDUCTIVE LAYER TO SELECTED PORTIONS OF A MOUNTING FRAME - A foam mount of an aircraft window has a groove to receive an electro chromic window. The foam mount is painted by placing a blank in the groove to divide the foam mount into a first section designated to face the exterior of the aircraft and an opposite second section. The groove and the first section are coated with an electric conductive paint, and the second section is covered with a decorative paint. The conductive coating on the foam mount and the conductive coating of the electrodes of the electro chromic window provide an RF shielding to prevent electronic signals from personal electronic equipment from passing through the cabin and door windows of the aircraft. A mask is also provided to coat one section of the foam mount while covering the other section. | 09-16-2010 |
20100308168 | AIRCRAFT FUSELAGE - An aircraft fuselage includes an exterior skin; at least one window frame; at least one window package disposed in a breakout of the exterior skin and attached to the at least one window frame; and a plurality of stiffening elements configured to stiffen the exterior skin, wherein at least one of the stiffening elements crosses the at least one window package. | 12-09-2010 |
20100320324 | FUSELAGE STRUCTURE FOR AIRCRAFT - The invention relates to the fuselage structure of an aircraft with an outer skin ( | 12-23-2010 |
20110017870 | SECTION OF AIRCRAFT FUSELAGE AND AIRCRAFT INCLUDING ONE SUCH SECTION - The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y. | 01-27-2011 |
20110017871 | LOAD-SUPPORTING AND DAMAGE-TOLERANT LAMINATED AIRCRAFT WINDOW - The invention relates to a vehicle window consisting of a transparent composite material, wherein the composite material comprises fibres and a matrix material such that the vehicle window is capable of withstanding structural loads occurring in the window region and can substantially provide the window function even in spite of damage to the vehicle window (damage-tolerant), the fibres and the matrix material being transparent and substantially having the same refractive index. The invention proposes vehicle windows which are damage-tolerant, load bearing, cost-saving, easy to handle and require less installation space than conventional vehicle windows. | 01-27-2011 |
20110024564 | INJECTION-MOLDED WINDOW PANEL AND RELATED METHODS - A window panel adapted for installation relative to a structure. The panel includes a single piece of generally transparent injection-molded material configured to span one or more openings in the structure. The panel has panel attachment inserts for attaching the panel relative to the structure. The inserts are embedded in the material alongside at least one edge of the panel. The panel has a curvature that essentially continues a curvature of the structure surrounding the opening(s) when the panel is installed relative to the structure. This panel can be single-pane and can provide an essentially continuous window along an aircraft fuselage. | 02-03-2011 |
20110042516 | WINDOW ELEMENT FOR A DOUBLE-SHELL SKIN FIELD OF AN AIRCRAFT FUSELAGE CELL - A window element for a double-shell skin field of an aircraft fuselage cell includes a window frame having a window module disposed in the frame, wherein the frame is disposed in an opening of the double-shell skin field, and wherein the frame is connected to the double-shell skin field by a surrounding embrasure profile positioned against a core structure of the skin field at least in some regions, wherein the core structure includes an inner and an outer covering layer. | 02-24-2011 |
20110155851 | AIRCRAFT OBSERVATION WINDOW - Aircraft observation window ( | 06-30-2011 |
20110186684 | WINDOW REPLACEMENT FOR FILLING A WINDOW FRAME - The invention relates to a window replacement for filling a window frame in an aircraft, in particular a passenger aircraft, the window replacement being fixable by means of a retainer in the window frame in place of the window assembly when the window assembly is removed. According to the invention, the window replacement comprises a panel-shaped element with at least a single curvature, the panel-shaped element, being made of a synthetic material. In one configurational variant, the window replacement according to the invention is formed by a monolithic panel-shaped element. In a second configurational variant, the panel-shaped element of the window replacement is formed by a sandwich panel. Both embodiments allow a weight reduction in comparison with a window replacement of a metallic material. | 08-04-2011 |
20120001025 | Device for fastening systems for an aircraft, adapted in particular to be used in relation to a window - The invention relates to a device for fastening systems in an aircraft. | 01-05-2012 |
20120112006 | METHOD OF APPLYING AN ELECTRIC CONDUCTIVE LAYER TO SELECTED PORTIONS OF A MOUNTING FRAME - A foam mount of an aircraft window has a groove to receive an electro chromic window. The foam mount is painted by placing a blank in the groove to divide the foam mount into a first section designated to face the exterior of the aircraft and an opposite second section. The groove and the first section are coated with an electric conductive paint, and the second section is covered with a decorative paint. The conductive coating on the foam mount and the conductive coating of the electrodes of the electro chromic window provide an RF shielding to prevent electronic signals from personal electronic equipment from passing through the cabin and door windows of the aircraft. A mask is also provided to coat one section of the foam mount while covering the other section. | 05-10-2012 |
20120119031 | Hybrid Frame Co-Mold Manufacture - A hybrid frame is fabricated by initially forming a stack of fibrous layers in an annular pattern. An annular metal trim is separately formed to conform with the annular pattern. The trim is trapped in a lower mold having a complementary lower mold channel. The stacked layers are trapped atop the trim in the lower mold channel. An upper mold is pressed atop the stacked layers for compression co-molding together in the lower mold the stacked layers and trim to co-form the hybrid frame. | 05-17-2012 |
20120193474 | Window Mounted Raft System - An inflatable life raft system for an aircraft includes a window coupled to a fuselage portion of the aircraft. A mechanism is used to selectively detach the window from the fuselage. An inflatable life raft is deployable to the exterior of the aircraft upon detachment of the window from the aircraft. | 08-02-2012 |
20120217345 | Observation port and a helicopter cabin - An observation port ( | 08-30-2012 |
20120217346 | FOAM WINDOW MOUNT HAVING AN ELECTRIC CONDUCTIVE LAYER OVER A LIGHT BLOCKING LAYER - A foam mount has a shape of an enclosed frame surrounding an open area, the frame in cross section having a peripheral surface; an inside surface opposite to the peripheral surface, the inside surface defining the open area. The inside surface includes a groove having an open end and the open end of the groove faces the open area of the foam mount. A coating is applied over selected surfaces of the foam mount, wherein the coating has a visible light transmission of less than 15%. Also disclosed is a method of coating an electric conductive coating over the visible light blocking coating and a decorative coating over selected surfaces of the foam mount. | 08-30-2012 |
20120228428 | HOOP LOAD BEARING AIRCRAFT TRANSPARENCY - An aircraft transparency includes a first ply having a first major surface and a second major surface. A second ply is spaced from the first ply and has a third major surface and a fourth major surface. A polymeric interlayer is located between the first and second plies. At least one bore extends through the first and second plies and the interlayer. A high strength bushing is located in the bore, with an outer sidewall of the bushing in direct contact with the material of the first and second plies. In one embodiment, the bore is a tapered bore and the bushing has a tapered outer sidewall. In another embodiment, the bore is a cylindrical bore and the bushing has a cylindrical outer sidewall. | 09-13-2012 |
20120241559 | Aircraft Window and Installation Method - An aircraft window has an inner window assembly retained on an outer window assembly by a plurality of interlocking clips and receptacles positioned around the perimeter of the window. The interlocking clips and receptacles produce a retention force that compresses a seal against an outer structural the window to seal an internal cavity between the inner and outer window assemblies. | 09-27-2012 |
20120256052 | WINDOW RING FOR AN AIRCRAFT WINDOW AND METHOD FOR THE PRODUCTION OF SAME - The invention relates to a window ring for a window of an aircraft, wherein the window ring is substantially formed of a light-guiding substrate, comprises at least one light inlet region to couple light into the substrate, and at least one light exit region which is formed in such a way that light coupled into the substrate exits in it. | 10-11-2012 |
20120267480 | Aircraft component comprising flame retardant compositions and methods of manufacture - An aircraft component wherein the component is a partition or a light cover, and wherein the aircraft component is molded or formed from a thermoplastic polymer composition including: a siloxane-containing copolymer in an amount effective to provide a total of 0.2 to 6.5 wt % of siloxane units based on the total weight of the polymers in the thermoplastic polymer composition, a bromine-containing polymer in an amount effective to provide 9 to 13 wt % of bromine, based on the total weight of the polymers in the thermoplastic polymer composition, and optionally a third polymer, wherein the wt % of the siloxane-containing copolymer, the bromine-containing polymer, and the optional third polymer, sum to 100 wt %, and 0.05 to 10 wt % of a light diffuser additive, based on the total weight of polymers in the thermoplastic polymer composition. | 10-25-2012 |
20130026296 | COCKPIT WINDOW OF AIRCRAFT HAVING ELECTROMAGNETIC SHIELD, AND AIRCRAFT - There is provided a cockpit window of an aircraft and the aircraft in which an electromagnetic shield film for preventing electromagnetic noise can be reliably and easily provided at low cost. An electromagnetic shield film is provided to a window part, and a conductive film is provided between the electromagnetic shield film and an outer retainer made of a conductive material. The conductive film is connected to the electromagnetic shield film via a connecting member is provided so as to be led to an outer perimeter side of the window part along an outer perimeter part of the window part, and is electrically connected to the outer retainer. With this configuration, a film made of a conductive material is formed without a gap at a joint portion between the window part and the outer retainer. Also, the conductive film is assumed to have flexibility. | 01-31-2013 |
20130043347 | Control System for Dimmable Windows - Electrically dimmable windows for aircraft are powered by energy harvesting devices on-board the aircraft. The harvested energy is stored and used to control the opacity of the windows based on individual window opacity settings selected either by passengers or a cabin attendant. Each window has an associated control circuit that controls the electrical power applied to the window based on the selected opacity setting. The control circuit includes a low energy usage processor that remains in a sleep mode until a change in the opacity setting is detected. Each control circuit may include a radio transceiver that receives control signals from a transmitter operated by the cabin attendant in order to simultaneously remotely control the opacity settings of multiple windows. | 02-21-2013 |
20130043348 | METHOD FOR ASSEMBLING WINDOW COAMING ON A FUSELAGE, COAMING TO BE USED, AND AIRCRAFT FUSELAGE PROVIDED WITH SUCH COAMING - A reduction of the multiple costs of manufacture, assembly use, and upkeep connected with the assembly of window frames on aircraft fuselages. To this end, the invention provides a particular shape for the frames connected to the fuselage skin according to a specific assembly method. The shape enables, among other things, the window frames to be fitted onto the skin by means of adhesion and also frames to be dispensed with between the fuselage and the window. In one embodiment, composite material window frame has a wall totally in the shape of a crown that is connected, through co-adhesion, to the inner surface of the fuselage skin, also made of composite material. The skin is cut into a window-receiving opening, and the frame has a T-shaped cross section, wherein the bar of the “T” that forms the crown includes two portions having substantially equal lengths “T.” | 02-21-2013 |
20130062468 | WINDOW OF AIRCRAFT, CLOSING MEMBER FOR OPENING AND GASKET SEAL - An electromagnetic shield mesh | 03-14-2013 |
20130168495 | NON-FOGGING VEHICLE WINDOW - A vehicle window with a primary window pane arrangement, a secondary window pane that is spaced apart from the primary window pane arrangement and a window funnel that extends between the secondary window pane and the primary window pane arrangement is provided. The vehicle window includes an intermediate space that is formed by the window funnel, the secondary window pane and the primary window pane arrangement, and the intermediate space is sealed and equipped with an air inlet for introducing dehumidified air into the intermediate space. Due to the seal, humid air leading to condensation and frost in the intermediate space is prevented from flowing into the intermediate space during a pressure compensation flow. The passenger comfort is enhanced due to the improved view through the window. | 07-04-2013 |
20130187005 | WINDOW FUNNEL AND WINDOW REGION FOR AN AIRCRAFT - A window funnel for an aircraft is provided, which has a ring made of an elastic material, which is arranged by means of an adhesive layer on an outer side of the window funnel, the ring having a hollow profile. The ring serves as a sight screen, light screen and dust screen for the rear side of the window funnel. | 07-25-2013 |
20130313366 | LOW DRAG PASSENGER-CABIN WINDOW - A low drag passenger-cabin window for use on an aircraft fuselage having a generally cylindrical shape, in which the as-manufactured geometry of the window is modified so that the shape of the window at cruise altitudes is aerodynamically optimized. The window comprises a pane of transparent material. The inner and outer surfaces of the peripheral portion of the pane as manufactured conform to a generally cylindrical shape, while the inner and outer surfaces of the medial portion of the pane as manufactured are depressed inwardly in a prescribed manner relative to the peripheral portion. The surfaces of the medial portion are adapted to deflect outwardly to conform to a generally cylindrical shape in response to a predetermined air pressure differential and/or a predetermined temperature gradient experienced at cruise altitude. | 11-28-2013 |
20130320143 | CABIN WINDOW WITH PLANNED DEFORMATION, METHOD OF MANUFACTURING SUCH A WINDOW AND AIRCRAFT COMPRISING SUCH A WINDOW - The present invention relates to an aircraft window, of the type including a holding frame for securing the window to the fuselage of an aircraft and at least one pane mounted in the holding frame by a sealing system, the at least one pane having an inner surface and an outer surface, characterized in that: the pane includes, in a first state called the rest state, at least one concavity in its outer surface when there is no pressure difference between the outer surface and the inner surface of the pane, and the at least one concavity of the pane is at least partially eradicated in a second state in which there is a pressure difference between the outer surface and the inner surface of the pane. | 12-05-2013 |
20140097295 | NOSE SECTION FOR A FLYING MACHINE AND ASSOCIATED FLYING MACHINE - The nose section for a flying machine according to the invention comprises an enclosure delimiting a nose cone extending along a longitudinal axis (A-A′), the enclosure delimiting a window, and a glass closing the window extending transversely relative to the longitudinal axis (A-A′). The nose section includes an optical sensor, in particular a camera, positioned in the enclosure behind the glass. The enclosure defines a recess, the window covered by the glass being at least partially positioned in the recess. | 04-10-2014 |
20140117160 | DECORATIVE RING DEVICE FOR FREE-FLOATING INTERFACE OF AIRCRAFT INTERIOR SIDEWALL WINDOW LINING - An interior lining interface incorporates a decorative interface ring having a substantially flat flange with multiple bearing ring bosses on an inner surface of the flange for engagement of an inner surface of a rim of a window ring. Multiple friction fit legs extend from the flange and are received within and constrained by the interface ring to the widow ring rim. A window reveal has a mating surface contacting the flange. | 05-01-2014 |
20140131516 | Aircraft window arrangement - An aircraft window arrangement comprising a sidewall lining panel which is provided with a window opening, an inner window attached to the sidewall lining panel and extending across the window opening formed in the sidewall lining panel and an outer window arranged at a distance from the inner window and extending across a window opening formed in an aircraft outer skin. The aircraft window arrangement further comprises a window funnel including an inner rim facing the inner window and extending along a circumference of the window opening formed in the sidewall lining panel, and an outer rim facing the outer window and extending along a circumference of the window opening formed in the aircraft outer skin. The window funnel is formed separate from the sidewall lining panel. The window funnel may be attached to a retainer for retaining the outer window. | 05-15-2014 |
20140209746 | WINDOW SHADING ASSEMBLY - A window shade assembly for a window includes a first member, a second member, a film, and an actuating device. The second member is disposed apart from the first member. The film has a first end coupled to the first member, a second opposed end coupled to the second member, an opaque portion, and a transparent portion. The actuating device is coupled to the first member or the second member for moving the first member or the second member to move the film between the first and the second members. | 07-31-2014 |
20140284425 | RADIO FREQUENCY SHIELDING SYSTEM - An assembly for shielding an aircraft from electromagnetic energy may include a window mounting configured to be conductively coupled to an aperture in a fuselage of an aircraft. The window mounting may include a window pane having an electromagnetically-reflective coating for reflecting electromagnetic energy. The window pane may remain electrically isolated from the fuselage prior to the electromagnetic energy exceeding a frequency of approximately 1 GHz. The window mounting may further include a capacitive gasket capcaitively coupling the window pane to the fuselage after the frequency of the electromagnetic energy reflected by the window pane exceeds approximately 1 GHz. | 09-25-2014 |
20140319276 | AIRCRAFT WINDOW AND AIRCRAFT - A window body constituting a window of an aircraft includes an electromagnetic shield film, and a conductive paint is applied to an outer perimeter edge face of the window body. A fixing member secures the window body to an airframe with a gasket seal and a window frame interposed therebetween. The fixing member has a first bonding surface on which a conductive film is formed. The first bonding surface is in direct contact with the gasket seal. An electrical path is formed through the electromagnetic shield film, the conductive paint, the gasket seal, the fixing member, and the window frame. | 10-30-2014 |
20140319277 | WINDOW OF AIRCRAFT, AIRCRAFT, AND ASSEMBLY METHOD FOR WINDOW OF AIRCRAFT - To easily and inexpensively provide a window of an aircraft having sufficient electromagnetic shielding performance and environment-resistant sealing performance, an aircraft, and an assembly method for a window of an aircraft. A conductive seal member | 10-30-2014 |
20140339365 | WINDOW OF AN AIRCRAFT - An aircraft includes a fuselage including a plurality of frame members disposed at predetermined intervals in a longitudinal direction of the fuselage and a plurality of stringers extending substantially linearly in the longitudinal direction. The fuselage defines an aircraft interior. A compartment is located in the interior of the fuselage. The compartment defines an interior area. A first one window assembly is mounted to an upper portion of the fuselage for introducing daylight into the interior area. The first window assembly is flanked by adjacent frame members of the plurality of frame members and adjacent stringers of the plurality of stringers. The first window assembly includes a window pane, an inner cover and a retainer. The inner cover introduces daylight from the window pane into the interior area. The retainer secures the window pane and the inner cover to the fuselage. | 11-20-2014 |
20150060603 | AIRCRAFT WINDOW, CLOSING MEMBER FOR OPENING PORTION, AND AIRCRAFT - An aircraft window includes: a window body including window panels, and an electromagnetic shield layer laminated on the window panels; a window frame that is made of a conductive material, and that surrounds the window body; a rubber-based gasket provided with conductivity, the gasket being at least partially held between the window body and the window frame; and a conductive layer that is located between the window body and the gasket, and that brings the electromagnetic shield layer and the gasket into conduction with each other. The window frame includes a holding section that holds the window body via the gasket from an airframe outer side. The conductive layer extends to a portion of the window body facing the holding section. | 03-05-2015 |
20160023746 | MODULAR INDEXING FOR AIRCRAFT INTERIOR - An assembly for an aircraft cabin of an aircraft, the aircraft having a fuselage with a plurality of external windows arranged at a pitch. The assembly having a window cone panel with an internal window, top and bottom edges defining a panel height, and side edges defining a panel width. First and second terminator components are disposed on either side of the window cone panel such that the first terminator component is on one side of the window cone panel and the second terminator component is on the other side of the window cone panel. A splice component is disposed on either side of the window cone panel between the window cone panel and one of the first and second terminator components. The splice component includes an index for adjusting an overall width of the assembly to align the internal window opening with the external window pitch. | 01-28-2016 |
20160031544 | GLASS PANEL FOR A SPACE AIRCRAFT - The invention relates to a glass panel for an aircraft suitable for a suborbital flight and an aeronautical flight, including an outer panel made of polycarbonate or aluminosilicate for temperature resistance, a main panel for pressure resistance, sized according to standard aeroplane safety factors, and an inner panel, providing redundancy for the main panel, sized with a minimum pressure margin, the outer, main and internal redundancy panels being separated from one another by spaces. The invention also relates to an aircraft including windscreen elements and portholes made using the glass panel. | 02-04-2016 |
20160101844 | FLIGHT DECK ARRANGEMENT - A flight deck arrangement includes, but is not limited to, a window. The flight deck arrangement further includes a surface disposed proximate the window and positioned below the window. The flight deck arrangement further includes a rail mounted to the surface. The rail is disposed proximate the window and positioned below the window. The rail extends along the surface in a direction generally aligned with a lower portion of the window. The flight deck arrangement still further includes a visor mounted to the rail and selectively positionable along the rail. | 04-14-2016 |
20160137282 | SOLAR WINDOW SHADE - A solar window shade for a window seat in an airliner for supplying electrical energy to charge a personal electronic device, including a window shade configured to cover a window, a solar panel attached to an outside face of the window shade, the solar panel facing outward to receive light from outside a passenger cabin, and a charging port incorporated into the window shade, the charging port electrically connected to the solar panel. | 05-19-2016 |
20160375980 | FUSELAGE SKIN WINDOW UNIT FOR AN AIRCRAFT - A fuselage skin window unit for an aircraft, an aircraft with such a fuselage skin window unit and a method for manufacturing such a fuselage skin window unit are described. The fuselage skin window unit includes a fuselage skin section and a window pane section. The fuselage skin section is part of a fuselage skin of the aircraft and has a pattern of pinhole perforations. The window pane section is transparent and arranged so that it covers the pinhole perforations. | 12-29-2016 |
20160376011 | AIRCRAFT AND AIRCRAFT WINDSHIELD HEATING SYSTEMS - Aircraft and aircraft windshield heating systems are provided. An aircraft windshield heating system includes a windshield, first and second heating elements, and a power bus controller. The windshield has a main portion and a reduced portion, the first and second heating elements are thermally coupled with the main portion and the reduced portion, respectively. The power bus controller is operatively coupled with the first heating element and the second heating element and is configured for coupling to a primary power supply and a backup power supply. The power bus controller is configured to determine when the primary power supply is available, to direct power from the primary power supply to the first heating element when the primary power supply is available, and to direct power from the backup power supply to the second heating element when the primary power supply is not available. | 12-29-2016 |