Windows Patents (Class 244/129.3)
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Publication number: 20080099615Abstract: A modular aircraft window includes an outer pane and an inner pane each inserted in a substantially rectangular frame. A foldable shade is disposed on one of the frames and has a freely movable end that is coupled with an operating unit for opening and closing the shade. The assembly further includes at least one shade raising and lowering mechanism in one or both of the longitudinal parts of the frame and a drive mechanism mounted in the lower transverse part of the frame. The drive mechanism includes a threaded spindle which, in order to provide for a particularly stable and long-lasting construction of the drive mechanism, is movable solely translationally and is coupled with a transmission mechanism operating the at least one raising and lowering mechanism.Type: ApplicationFiled: May 11, 2007Publication date: May 1, 2008Inventors: Gottfried Steiner, Mario Staubmann
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Publication number: 20080078878Abstract: A window frame (1) for installation in the exterior (5) of an aircraft, which comprises in each case at least one outer flange (2), one inner flange, and one vertical flange (4) arranged perpendicular between these flanges, is manufactured from a fiber-reinforced synthetic resin, in which, first, a semifinished part comprising fiber material is inserted into a molding tool, in which, under pressure and 2 temperature, resin is injected, and subsequently, the component made in this manner is hardened in the molding tool. The semifinished part can have a layer structure either made from a webbing material, from fiber bundles, or from a combination of fiber bundles and a webbing material.Type: ApplicationFiled: May 24, 2005Publication date: April 3, 2008Applicant: AIRBUS DEUTSCHLAND GMBHInventor: Jens Bold
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Publication number: 20080078876Abstract: A composite resin window frame for installation in a composite resin airplane fuselage has an inner flange for receiving and securely affixing an aircraft window transparency and an outer flange adapted for connection to the airplane fuselage structure. The frame has a generally flat configuration which does not require any additional strength enhancing member such as an additional flange perpendicular to the structure. The composite resin window frame has sufficient strength to securely affix a window transparency to a composite resin fuselage.Type: ApplicationFiled: August 15, 2006Publication date: April 3, 2008Inventors: Phillip D. Baggette, Richard W. Brigman, Bernhard Dopker, Robert W. Johnson, Jeffery P. Sandys
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Publication number: 20080078877Abstract: A window assembly for a mobile platform, for example, a commercial aircraft. The window assembly includes a reveal member that is retained within an opening in an interior panel of the mobile platform without the use of independent retaining clips or adhesives. In one embodiment the reveal member is generally rectangular in shape and includes a flange adjacent to each of the four corners thereof. The flanges engage the opening in the structural panel so that the reveal member can be held in a precise position within the opening in the interior structural panel without external fastening clips or adhesives. The window assembly is lighter in weight than existing window assemblies, and can also be easily removed without special tools or disassembly procedures, and also is retrofittable to existing mobile platforms.Type: ApplicationFiled: August 24, 2006Publication date: April 3, 2008Inventors: Lon E. Switzer, Robert D. Dixon, Fred P. Seibert, Scott Laverne, Michael J. Zizzo, Gregory W. Nelson, Gennady V. Shankov, James G. Trimble
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Patent number: 7350753Abstract: Disclosed is an improved aircraft window having RF shielding. In one embodiment, a window shield comprises an electrically conductive, transparent, flexible film, which is applied by known processes to a window pane. This shield is grounded to the aircraft frame or exterior by a “tail” of conductive material, which is secured to a ground point in the vicinity of the window pane.Type: GrantFiled: July 21, 2005Date of Patent: April 1, 2008Assignee: Row 44, Inc.Inventors: John Guidon, Gregg Fialcowitz
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Publication number: 20080067288Abstract: 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.Type: ApplicationFiled: September 13, 2007Publication date: March 20, 2008Inventors: Ulrich Eberth, Mario Koeber
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Patent number: 7303700Abstract: An optically clear structural laminate includes a thermosetting resin, a silane coupling agent and a filler. The laminate has a high weight to strength ratio and is capable of optical transmission over a wide range of temperatures. The laminate has increased tensile strength and is capable of being easily formed into complex shaped components. The structural properties of the laminate make it useful as aircraft canopies and windows.Type: GrantFiled: August 31, 2004Date of Patent: December 4, 2007Assignee: The Boeing CompanyInventors: Michael C. Miller, Timothy J. Krey, Donald J. Bridges, James L. Melquist
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Patent number: 7300693Abstract: A transparent skin panel for use in a mobile platform having a plurality of metal sheets. A fiber reinforced resin at least partially surrounds the plurality of metal sheets. The fiber reinforced resin is transparent. A cutout is formed within each of the plurality of metal sheets, which is filled by the transparent resin during the manufacturing process. The cutout corresponds to a window in the transparent skin panel. The transparent skin panel thus eliminates the need for a bulky and heavy frame structure that has traditionally been employed on aircraft, and which has heretofore limited the size of windows used on an aircraft. The present invention thus enables larger windows to be incorporated on aircraft without increasing the weight or cost associated with such windows.Type: GrantFiled: September 4, 2003Date of Patent: November 27, 2007Assignee: The Boeing CompanyInventors: Robert G Albers, Paul S Nordman
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Patent number: 7286289Abstract: A surveillance window including at least one set of linear polarizer and quarter-waveplate and a reflecting surface. The surveillance window appears dull and opaque to a subject, while allowing a relatively high percentage of light to be transmitted to an observer. Various enhancements including an illuminator and detector, camouflaging, fire resistance, and improvements to the opacity are also described.Type: GrantFiled: March 5, 2007Date of Patent: October 23, 2007Assignee: Thales Avionics, Inc.Inventors: Xavier Bengoechea, Francesco Finizio, Richard Grich
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Patent number: 7281686Abstract: A window assembly for an aircraft fuselage comprises an exterior transparent panel and an interior transparent panel positioned in an opening of the fuselage. At least one of the transparent panels may be relatively lightweight and the exterior transparent panel may be spaced apart from and in overlying relationship with the interior transparent panel. To ameliorate pressure build up in the spaced apart area, a pressure modulator, such as a vent, may be provided.Type: GrantFiled: November 2, 2005Date of Patent: October 16, 2007Assignee: The Boeing CompanyInventor: Jeffrey H. Wood
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Patent number: 7267302Abstract: A device that alters the breather hole configuration currently being employed in aircraft window assemblies. The device provides a means to allow slow moving air to pass and breathe through the breather hole, while stopping or significantly blocking non-steady air pulses from passing through. The device uses a combination of the cross-section and length of the air path that determines the effectiveness of the particular device to dampen out any unsteady airflow pulses.Type: GrantFiled: March 29, 2005Date of Patent: September 11, 2007Assignee: The Boeing CompanyInventors: Craig E. Coak, Joel E. Hansen
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Patent number: 7187498Abstract: A surveillance window including at least one set of linear polarizer and quarter-waveplate and a reflecting surface. The surveillance window appears dull and opaque to a subject, while allowing a relatively high percentage of light to be transmitted to an observer. Various enhancements including an illuminator and detector, camouflaging, fire resistance, and improvements to the opacity are also described.Type: GrantFiled: May 28, 2002Date of Patent: March 6, 2007Assignee: Thales Avionics, Inc.Inventors: Xavier Bengoechea, Francesco Finizio, Richard Grich
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Patent number: 7143979Abstract: An injection molded windshield is provided for a vehicle. The injection molded acrylic or polycarbonate windshield enables vehicle shape design flexibility while achieving lower aerodynamic drag. The injection molded windshields offer additional benefits for the crew by increasing visibility area with larger windshields while reducing aero noise. The vehicle includes a body and an injection molded window attached to the body. The injection molded windshield is shaped to conform to the fuselage. The injection molded windshield is formed of at least one of an injection molded acrylic or polycarbonate material. The injection molded windshield is impact and ballistic tolerant.Type: GrantFiled: May 30, 2003Date of Patent: December 5, 2006Assignee: The Boeing CompanyInventors: Jeffrey H. Wood, Terry A. Sewell
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Patent number: 7118070Abstract: A window assembly incorporating a composite seal is provided. The composite seal has a first sealing member and a second member stiffer than the first sealing member.Type: GrantFiled: July 23, 2004Date of Patent: October 10, 2006Assignee: Sierracin CorporationInventors: Mark D. Abrams, Robert M. Smith
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Patent number: 7118069Abstract: A system and a method is provided for fitting an aircraft cabin with modular sidewall panels, window reveals, and foam insulation blocks in an integrated manner. The system comprises a sidewall panel which may have one or more openings therethrough to receive a window reveal held by snap-fit fastenings. The bezel of the window reveal may be held by snap-fit fasteners for easy removal to allow removal and cleaning of the inner dust cover disassembly of the sidewall panel. Foam insulation blocks may be molded to fit in the cavity between the outer wall of the aircraft and the sidewall panels, held in place by compressive pressure between the frames of the airframe. The outer extent of the window reveal is tapered inwardly to guide the window reveal to mating contact with an outer window assembly in the aircraft fuselage without further adjustment of the sidewall panel.Type: GrantFiled: December 2, 2004Date of Patent: October 10, 2006Assignee: The Boeing CompanyInventors: Keith H. Novak, Robert W. Mumm, Karen L. Hills, Joe S. Wong, Shawn M. Pare, Julia W. Miller, Art Waidner
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Patent number: 7080807Abstract: A window assembly incorporating a window frame and seal and a method of forming the same are provided. The window assembly includes a window transparency first ply coupled to a first window structure. A window transparency second ply is coupled to the first ply and is spaced apart from the first structure defining a gap there between. A portion of the first structure, or a second window structure coupled to the first structure, extends over the second ply. A seal is placed, fitted or formed within the gap and between the second ply and the portion of the first structure or the second structure extending over the second ply.Type: GrantFiled: February 26, 2004Date of Patent: July 25, 2006Assignee: Sierracin CorporationInventors: Jan B. Olson, Mike H. Robson
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Patent number: 7040577Abstract: An apparatus and method for latching a canopy to a vehicle, such as an aircraft, that avoids plastic creep and crazing due to concentrated loads is provided. The apparatus includes first attachment components that are at least partially embedded within an injection-molded canopy and second attachment components that are connected to the canopy rail for attaching to the one or more first attachment components and thereby attaching the canopy to the canopy rail.Type: GrantFiled: October 7, 2004Date of Patent: May 9, 2006Assignee: The Boeing CompanyInventors: Jeffrey H. Wood, Terry A. Sewell, Steven J. Miener
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Patent number: 7028950Abstract: A substantially strong, lightweight load bearing window for use in a mobile platform, for example, an aircraft. The window includes a rim portion having a carbon reinforced resin structure and a transparent portion having a fiberglass reinforced resin structure. A plurality of holes are formed in the rim portion for enabling a plurality of connectors to be inserted therethrough. The rim portion has a smaller cross sectional area (i.e., thickness) than the transparent portion such that the rim portion is adapted to fit behind a skin of an aircraft, the transparent portion is adapted to be flush with the skin of the aircraft. The connectors fix the window to the skin of the aircraft. The window effectively forms a strong, structurally integral portion of the skin.Type: GrantFiled: May 10, 2004Date of Patent: April 18, 2006Assignee: The Boeing CompanyInventors: James J. Salmon, Scot McKee
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Patent number: 6938858Abstract: A spacecraft window assembly for providing external viewing from inside an inflatable module is claimed. The inflatable shell has a plurality of layers and each layer has a window opening. The spacecraft window assembly comprises a body, a window assembly window opening, and at least one pressure pane disposed within, and forming a substantially airtight seal with, the window assembly. The body of the window assembly is adapted for securedly receiving each one of the plurality of layers of the inflatable shell to the body of the window assembly such that the window opening in each layer of the inflatable shell is substantially aligned with the pressure pane. Further, the body of the window assembly is adapted to form a substantially air tight seal with at least one layer of the inflatable shell.Type: GrantFiled: June 24, 2004Date of Patent: September 6, 2005Assignee: Bigelow AerospaceInventors: William C. Schneider, Edwin E. Lardizabal
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Patent number: 6915988Abstract: Windows, including windows for an aircraft. The windows include a shade. The shade has variable light transmissive characteristics. The shade is entrained upon rollers so that it may roll across the lens window. The parts of the shade are nearly opaque and other parts are nearly transparent. The result is a shade that has varying optical density depending upon the position of the hand operated rollers or shade positioning mechanism.Type: GrantFiled: January 27, 2004Date of Patent: July 12, 2005Assignee: MSA Aircraft Products, Ltd.Inventors: Eduardo Sanz, Gilbert Moreno
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Patent number: 6915987Abstract: The invention relates to a method of providing a seal between an aircraft structure (14) and a removable panel (26) mountable on the structure to close an opening (12) therein. According to the invention, the method comprises applying a sealant compound (28) for example a polysulphide rubber compound, to one of the structure and the panel, forming a rebate (46) in the sealant compound, and providing a sealant tape (48) to fit within the rebate. Subsequently, the panel is fastened to the structure with the seal (50) comprising the sealant compound and the sealant tape being sandwiched between the structure and the panel and encircling the opening.Type: GrantFiled: September 11, 2002Date of Patent: July 12, 2005Assignee: BAE Systems plc.Inventors: David Fisher, Raja S. Abbas, John S. Robbens, Stan Wood
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Patent number: 6905094Abstract: Device for attachment of an aircraft windshield. The device comprises a monoblock flange (14). The flange is fixed to the structure (12) of the aircraft by screws (16), so as to trap a peripheral edge of the windshield glass (10) between the flange and the structure. A dry monoblock seal (18) surrounds the peripheral edge of the windshield, such that the seal alone provides leak tightness between the inside and the outside of the aircraft. Preferably, the screws (16) are in contact with the flange (14) through plane surfaces perpendicular to the center lines of the screws. At least one second dry monoblock seal (20) may also be placed between the flange (14) and the structure (12).Type: GrantFiled: October 2, 2002Date of Patent: June 14, 2005Assignee: Airbus FranceInventors: Francis Dazet, Pascal Chaumel, Guy Cavailles, Jean-Christian Beucher
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Patent number: 6889938Abstract: A window adapted to be integrally formed with a skin of an aircraft having a first transparent fiberglass layer, a second transparent fiberglass layer, and a transparent epoxy layer. The transparent epoxy layer is located between the first and second transparent fiberglass layers. A glass outer-pane is removably coupled to the first transparent fiberglass layer such that the glass outer-pane covers the first transparent fiberglass layer. The first and second transparent fiberglass layers have an index of refraction approximately matching an index of refraction of the transparent epoxy layer. The first and second transparent fiberglass layers are adapted to be integrally formed with the skin of the aircraft.Type: GrantFiled: October 21, 2003Date of Patent: May 10, 2005Assignee: The Boeing CompanyInventor: Paul S. Nordman
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Patent number: 6883755Abstract: An aircraft cockpit window comprises a window pane (12) fitted with a frame (14), and guide rails (16, 18) on which the frame (14) is guided at three points (A, B, C) using two lower sets of rollers (20, 22) and an upper set of rollers (24). All these controls for locking/unlocking and opening the window pane are grouped on a handle (26) articulated on the lower edge of the frame (14), about an axis (28) that is preferably approximately vertical.Type: GrantFiled: November 24, 2003Date of Patent: April 26, 2005Assignee: Airbus FranceInventors: Olivier Pautis, Francis Dazet, Pascal Chaumel
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Patent number: 6874733Abstract: A latching system and method for a canopy are provided. Devices are partially embedded in the canopy and latches are slideably received within a canopy rail of the vehicle. The latches are controlled by a latch controller and lock the canopy to the vehicle. A canopy position sensor senses the position of the canopy, and a canopy controller controls the position of the canopy. The latch controllers control the position of the one or more latches based on the sensed position of the canopy or the status of the canopy controller. A latch position sensor senses the position of the latches and a vehicle position sensor senses the position of the vehicle. The canopy controller controls the position of the canopy based on the sensed position of the latches and the sensed position of the vehicle.Type: GrantFiled: February 13, 2003Date of Patent: April 5, 2005Assignee: The Boeing CompanyInventor: Jeffrey H. Wood
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Patent number: 6874732Abstract: A ceramic element, e.g., a sapphire dome, is joined to a metallic element, e.g., a vehicle body comprising a titanium alloy, by an attachment structure, e.g., comprising niobium. The attachment structure comprises: (1) a form-factored, compliant metallic transition element having a “C” shape; (2) a first joint material connecting an upper portion of the transition element to the ceramic element; and (3) a second joint material connecting a lower portion of the transition element to the metallic element. A method is provided for attaching the ceramic element to the metallic element, using a single brazing operation. The presence of the attachment structure further minimizes the stresses related to the different coefficients of thermal expansion in the ceramic/attachment/titanium connection.Type: GrantFiled: December 4, 2002Date of Patent: April 5, 2005Assignee: Raytheon CompanyInventors: Quenten E. Duden, Wayne L. Sunne, James H. Gottlieb
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Patent number: 6848655Abstract: An apparatus and method for attaching an injection-molded canopy to a hinge assembly is provided. The apparatus includes attachment components that are at least partially embedded in the injection-molded canopy. A hinge assembly attaches to the attachment components for controlling the position of the canopy. The canopy is a polycarbonate or acrylic frameless canopy. The hinge assembly is hingedly attached to the vehicle. The hinge assembly includes a center support and port and starboard supports. The center support is located approximately along a centerline of the canopy, the port support is located on a port side of the vehicle, and the starboard support is located on a starboard side of the vehicle.Type: GrantFiled: February 13, 2003Date of Patent: February 1, 2005Assignee: The Boeing CompanyInventor: Jeffrey H. Wood
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Publication number: 20040262453Abstract: Windows, including windows for an aircraft. The windows include a shade. The shade has variable light transmissive characteristics. The shade is entrained upon rollers so that it may roll across the lens window. The parts of the shade are nearly opaque and other parts are nearly transparent. The result is a shade that has varying optical density depending upon the position of the hand operated rollers or shade positioning mechanism.Type: ApplicationFiled: January 27, 2004Publication date: December 30, 2004Applicant: MSA Aircraft Interior Products, Ltd.Inventors: Eduardo Sanz, Gilbert Moreno
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Publication number: 20040238690Abstract: An injection molded windshield is provided for a vehicle. The injection molded acrylic or polycarbonate windshield enables vehicle shape design flexibility while achieving lower aerodynamic drag. The injection molded windshields offer additional benefits for the crew by increasing visibility area with larger windshields while reducing aero noise. The vehicle includes a body and an injection molded window attached to the body. The injection molded windshield is shaped to conform to the fuselage. The injection molded windshield is formed of at least one of an injection molded acrylic or polycarbonate material. The injection molded windshield is impact and ballistic tolerant.Type: ApplicationFiled: May 30, 2003Publication date: December 2, 2004Inventors: Jeffrey H. Wood, Terry A. Sewell
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Patent number: 6817571Abstract: Aircraft having cab portions with integrated windshields are disclosed. The cab portion can include a rounded nose and a windshield positioned above and aft of a forward extremity of the rounded nose. A contour of the cab portion extending from the nose over the windshield aft of the nose can have a generally continuously smooth, unkinked shape. In particular embodiments, the portion of the contour corresponding to the windshield can be convex when viewed from a position external to the cab portion, and the shape of the windshield can form a portion of a conical surface.Type: GrantFiled: October 8, 2003Date of Patent: November 16, 2004Assignee: The Boeing CompanyInventors: Kevin M. Retz, Nicholaas Voogt, Michael G. Friend, Christopher R. Holtorf, Mannon L. Wallace, Andrew Sones
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Patent number: 6793182Abstract: A readily attachable window assembly for efficient installation and maintenance of aircraft windows is provided. The aircraft has a sidewall having an inner perimeter that defines an opening. The window assembly includes an outer window frame. A center window frame is attached to the outer window frame, and an inner window frame is attached to the center window frame. The inner window frame is readily attachable to the sidewall adjacent to the opening of the inner perimeter. The inner window frame includes a releasable coupling mechanism that includes first and second engaging mechanisms that positionally lock the first mechanism to the second mechanism via a torsion spring assembly and engageable teeth of each mechanism. The first engaging mechanism is locked onto the sidewall when torque is applied through at least one pinhole. The window assembly is disengaged by disengaging the first and second engaging mechanisms via a disengagement tab.Type: GrantFiled: March 25, 2002Date of Patent: September 21, 2004Assignee: The Boeing CompanyInventors: Jonathan L. Hopkins, Paul A. Ely, Edward H. Chue
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Patent number: 6789765Abstract: A readily attachable window assembly for efficient installation and maintenance of aircraft windows is provided. The aircraft has a sidewall having an inner perimeter that defines an opening. The window assembly includes an outer window frame. A center window frame is attached to the outer window frame, and an inner window frame is attached to the center window frame. The inner window frame is readily attachable to the sidewall adjacent to the opening of the inner perimeter. The inner window frame includes a releasable coupling mechanism that includes first and second engaging mechanisms that positionally lock the first mechanism to the second mechanism via a torsion spring assembly and engageable teeth of each mechanism. The first engaging mechanism is locked onto the sidewall when torque is applied through at least one pinhole. The window assembly is disengaged by disengaging the first and second engaging mechanisms via a disengagement tab.Type: GrantFiled: September 30, 2003Date of Patent: September 14, 2004Assignee: The Boeing CompanyInventors: Jonathan L. Hopkins, Paul A. Ely, Edward H. Chue
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Patent number: 6786453Abstract: An aircraft window assembly with a readily attachable window assembly for efficient and easy installation and maintenance of aircraft windows. The aircraft has a sidewall having an inner perimeter that defines an opening. An inner window frame is readily attachable to the sidewall adjacent to the inner perimeter. The inner window frame defines a first opening. An outer window frame is readily attachable to the inner window frame adjacent the first opening and the outer window frame defines a second opening. The outer window frame and the inner window frame are releasably coupled within the first opening of the inner window frame. The snap-in window assembly is readily detachable from the sidewall adjacent to the inner perimeter.Type: GrantFiled: October 25, 2001Date of Patent: September 7, 2004Assignee: The Boeing CompanyInventor: Gary E. Jones
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Patent number: 6783099Abstract: An electrochromic aircraft window assembly includes: a) an outboard pane assembly; and b) a fog preventing electrochromic pane assembly spaced from the outboard pane assembly and defining a chamber therebetween, the fog preventing electrochromic pane assembly having: i) a first substrate having a first surface including a first conductive coating and a second surface including a second conductive coating; ii) a second substrate spaced from the first substrate, the second substrate having a first surface including a third conductive coating, the second surface of the first substrate and the first surface of the second substrate facing each other in spaced-apart relation to define a chamber therebetween; iii) an electrochromic medium contained in the chamber and in contact with the second and the third conductive coatings, the electrochromic medium having a luminous transmittance that varies upon application of an electrical potential through the electrochromic medium; iv) facilities for applying electrical curType: GrantFiled: May 12, 2003Date of Patent: August 31, 2004Assignee: PPG Industries Ohio, Inc.Inventors: Thomas G. Rukavina, Chia-Cheng Lin
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Publication number: 20040104306Abstract: An aircraft cockpit window comprises a window pane (12) fitted with a frame (14), and guide rails (16, 18) on which the frame (14) is guided at three points (A, B, C) using two lower sets of rollers (20, 22) and an upper set of rollers (24). All these controls for locking/unlocking and opening the window pane are grouped on a handle (26) articulated on the lower edge of the frame (14), about an axis (28) that is preferably approximately vertical.Type: ApplicationFiled: November 24, 2003Publication date: June 3, 2004Inventors: Olivier Pautis, Francis Dazet, Pascal Chaumel
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Patent number: 6736352Abstract: Aircraft windows and associated methods for installation. The windows can be installed in a passenger cabin of an aircraft and can include a frame that supports a pane assembly having a viewing area of at least 180 square inches. The viewing area can have a triangular shape, with the sides of the window aligned with none of the major axis of the aircraft. Alternatively, the window can have a longitudinally extended rectangular shape, a diamond shape or an elliptical shape. The window frame can have a divider portion that separates two window apertures, each of which carries a separate pane assembly. Adjacent windows can be closed out with a common bezel.Type: GrantFiled: June 25, 2002Date of Patent: May 18, 2004Assignee: The Boeing CompanyInventors: Ralph Bladt, Joseph P. Condon, Richard Fraker, Domenic S. Giuntoli, Paul Mikulencak, William Quan, Michael A. Ritts, Ryon Christopher Warren
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Publication number: 20040065777Abstract: A readily attachable window assembly for efficient installation and maintenance of aircraft windows is provided. The aircraft has a sidewall having an inner perimeter that defines an opening. The window assembly includes an outer window frame. A center window frame is attached to the outer window frame, and an inner window frame is attached to the center window frame. The inner window frame is readily attachable to the sidewall adjacent to the opening of the inner perimeter. The inner window frame includes a releasable coupling mechanism that includes first and second engaging mechanisms that positionally lock the first mechanism to the second mechanism via a torsion spring assembly and engageable teeth of each mechanism. The first engaging mechanism is locked onto the sidewall when torque is applied through at least one pinhole. The window assembly is disengaged by disengaging the first and second engaging mechanisms via a disengagement tab.Type: ApplicationFiled: September 30, 2003Publication date: April 8, 2004Inventors: Jonathan L. Hopkins, Paul A. Ely, Edward H. Chue
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Patent number: 6688556Abstract: The invention relates to transport techniques and can be used for protecting passengers and a pilot in a cabin of an aircraft or another transport means against intense light, in addition to an auxiliary arrangement for moving mobile furniture elements. The dimming device comprises a blind and a mechanism for moving the blind, including guides for translational displacement of the blind and axial connecting elements of said mechanism. Intermediate non-rigid elements like, for example, a self-adhesive gearing band are arranged between contacting surfaces of the blind and the guides. The device ensures smooth displacement of the blind by means of decreasing friction force between the contacting elements and reduces noise occurring while the device is in use.Type: GrantFiled: May 28, 2002Date of Patent: February 10, 2004Assignee: Inter AMI Ltd.Inventors: Logvinenko Yuriy, Pidpruzhnikov Vladyslav
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Publication number: 20030234322Abstract: Aircraft windows and associated methods for installation. The windows can be installed in a passenger cabin of an aircraft and can include a frame that supports a pane assembly having a viewing area of at least 180 square inches. The viewing area can have a triangular shape, with the sides of the window aligned with none of the major axis of the aircraft. Alternatively, the window can have a longitudinally extended rectangular shape, a diamond shape or an elliptical shape. The window frame can have a divider portion that separates two window apertures, each of which carries a separate pane assembly. Adjacent windows can be closed out with a common bezel.Type: ApplicationFiled: June 25, 2002Publication date: December 25, 2003Inventors: Ralph Bladt, Joseph P. Condon, Richard Fraker, Domenic S. Giuntoli, Paul Mikulencak, William Quan, Michael A. Ritts, Ryon Christopher Warren
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Publication number: 20030192991Abstract: An electrochromic aircraft window assembly includes: a) an outboard pane assembly; and b) a fog preventing electrochromic pane assembly spaced from the outboard pane assembly and defining a chamber therebetween, the fog preventing electrochromic pane assembly having: i) a first substrate having a first surface including a first conductive coating and a second surface including a second conductive coating; ii) a second substrate spaced from the first substrate, the second substrate having a first surface including a third conductive coating, the second surface of the first substrate and the first surface of the second substrate facing each other in spaced-apart relation to define a chamber therebetween; iii) an electrochromic medium contained in the chamber and in contact with the second and the third conductive coatings, the electrochromic medium having a luminous transmittance that varies upon application of an electrical potential through the electrochromic medium; iv) facilities for applying electrical curType: ApplicationFiled: May 12, 2003Publication date: October 16, 2003Inventors: Thomas G. Rukavina, Chia-Cheng Lin
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Patent number: 6633239Abstract: A warning indication system and method of using the same in conjunction with a cargo door of an aircraft. The cargo door is positionable in an opened position; a closed position; a closed and latched position; and a closed, latched, and locked position. The method includes outputting first and second closed signals when the cargo door is in the closed position; outputting first and second latched signals when the cargo door is in the closed and latched position; and outputting first and second locked signals when the cargo door is in the closed, latched, and locked position. All of the signals are then analyzed to positively determine the position of the cargo door, while minimizing the probability of false indications. Various warnings are generated in response to the combination of signals received. The apparatus employs a dual logic system and redundant sensors to provide differing warnings dependent on the phase of flight.Type: GrantFiled: July 17, 2001Date of Patent: October 14, 2003Assignee: The Boeing CompanyInventors: Leo W. Plude, Todd B. Brouwer, Mark E. Brighton, Donald E. Ham
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Publication number: 20030178531Abstract: A readily attachable window assembly for efficient installation and maintenance of aircraft windows is provided. The aircraft has a sidewall having an inner perimeter that defines an opening. The window assembly includes an outer window frame. A center window frame is attached to the outer window frame, and an inner window frame is attached to the center window frame. The inner window frame is readily attachable to the sidewall adjacent to the opening of the inner perimeter. The inner window frame includes a releasable coupling mechanism that includes first and second engaging mechanisms that positionally lock the first mechanism to the second mechanism via a torsion spring assembly and engageable teeth of each mechanism. The first engaging mechanism is locked onto the sidewall when torque is applied through at least one pinhole. The window assembly is disengaged by disengaging the first and second engaging mechanisms via a disengagement tab.Type: ApplicationFiled: March 25, 2002Publication date: September 25, 2003Inventors: Jonathan L. Hopkins, Paul A. Ely, Edward H. Chue
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Patent number: 6619590Abstract: A connecting device for joining a windshield with a fuselage side frame of a viewing port of an aircraft, especially a cockpit frame of a helicopter. The connecting device includes a fastening element which is fixed into position on a section of a peripheral region of the windshield through a bore hole and into a congruent bore hole of the fuselage side frame and in a fastening part with a spring device. A peripheral slit filled with a sealant is arranged in a peripheral region between the fuselage side frame and windshield. The fastening part includes a retaining nut and a spring device which can be moved and guided within a seating element and connected with the fuselage side frame. The spring device is arranged between the retaining nut and the frame.Type: GrantFiled: June 27, 2002Date of Patent: September 16, 2003Assignee: Eurocopter Deutschland GmbHInventors: Klaus Wojatschek, Mark Drewe
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Patent number: 6601799Abstract: An aircraft passenger cabin window construction is formed by a casing of modular elements that are easily assembled and permit using substantially larger inner window panes compared to the area size of outer window panes thereby avoiding forming a funnel configuration or effect. For this purpose a window sill (8) is provided with lateral upward extensions (8B) and (8C) to provide a U-configuration that is held in place by casing elements (6) and (7). The casing elements (6, 7) may simultaneously form inner cabin wall panels and also reach upwardly with extensions (6A) and (7A) to form a further U-configuration cooperating with the first mentioned U-configuration of the sill (8). The upper open end of the two U-configurations is closed by a casing element (10). An inner window pane is supported or covered by the window sill. A central casing element (9) extending vertically may divide the U-shaped configurations into at least two sections.Type: GrantFiled: April 10, 2002Date of Patent: August 5, 2003Assignee: Airbus Deutschland GmbHInventors: Michael Lau, Sven Schaich
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Patent number: 6592077Abstract: A window for an aircraft door includes an outer pane, an inner pane, and a Fresnel lens element provided in the interspace formed between the inner and outer panes. The Fresnel lens element may be a self-supporting lens element pane positioned intermediately within the interspace between the inner and outer panes, or a lens film adhesively bonded onto the surface of the inner pane facing the interspace, or a Fresnel lens configuration provided directly on the surface of the inner pane facing the interspace. The Fresnel lens element provides an expanded field of view, especially in a downward direction, when looking out through the window, to comply with safety regulations that require visual inspection of the area outside of the aircraft door and especially below the door, before opening the door.Type: GrantFiled: September 19, 2001Date of Patent: July 15, 2003Assignee: Airbus Deutschland GmbHInventors: Sven Uhlemann, Michael Race
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Patent number: 6561460Abstract: An electrochromic aircraft window assembly includes: a) an outboard pane assembly; and b) a fog preventing electrochromic pane assembly spaced from the outboard pane assembly and defining a chamber therebetween, the fog preventing electrochromic pane assembly having: i) a first substrate having a first surface including a first conductive coating and a second surface including a second conductive coating; ii) a second substrate spaced from the first substrate, the second substrate having a first surface including a third conductive coating, the second surface of the first substrate and the first surface of the second substrate facing each other in spaced-apart relation to define a chamber therebetween; iii) an electrochromic medium contained in the chamber and in contact with the second and the third conductive coatings, the electrochromic medium having a luminous transmittance that varies upon application of an electrical potential through the electrochromic medium; iv) facilities for applying electrical curType: GrantFiled: July 31, 2001Date of Patent: May 13, 2003Assignee: PPG Industries Ohio, Inc.Inventors: Thomas G. Rukavina, Chia-Cheng Lin
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Publication number: 20030080252Abstract: An aircraft window assembly with a readily attachable window assembly for efficient and easy installation and maintenance of aircraft windows is provided. The aircraft has a sidewall having an inner perimeter that defines an opening. An inner window frame is readily attachable to the sidewall adjacent to the inner perimeter. The inner window frame defines a first opening. An outer window frame is readily attachable to the inner window frame adjacent the first opening and the outer window frame defines a second opening. The outer window frame and the inner window frame are releasably coupled within the first opening of the inner window frame. The snap-in window assembly is readily detachable from the sidewall adjacent to the inner perimeter.Type: ApplicationFiled: October 25, 2001Publication date: May 1, 2003Inventor: Gary E. Jones
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Publication number: 20030062450Abstract: Device for attachment of an aircraft windshield.Type: ApplicationFiled: October 2, 2002Publication date: April 3, 2003Inventors: Francis Dazet, Pascal Chaumel, Guy Cavailles, Jean-Christian Beucher
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Publication number: 20030015624Abstract: A window apparatus for use within an aircraft interior. This window having at least one shade frame, at least one shade attached to the shade frame at its top and a moveable shade rail attached at its bottom, a first and second lens assembly where the first lens assembly has first lens and the second lens assembly has a second lens, the first and second lenses being mountable to the shade frame such that they form a double convex configuration, and means for moving the shade between a substantially open position and a substantially closed position.Type: ApplicationFiled: September 19, 2002Publication date: January 23, 2003Applicant: MSA AIRCRAFT PRODUCTS, L.P.Inventors: Eduardo Sanz, Gilbert Moreno
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Patent number: 6493128Abstract: A chromogenic window panel assembly, and a chromogenic skylight each includes an outer panel and a chromogenic member having an optical property which varies according to an applied signal. A chromogenic light pipe includes a light harvesting member and a chromogenic member having an optical property which varies according to an applied signal. A chromogenic vehicle sunroof, a chromogenic aircraft window assembly, and a chromogenic window assembly each includes a panel having a particular panel contour corresponding to a surface contour and a chromogenic panel having an optical property which varies according to an applied signal. A chromogenic block includes two panels and a chromogenic panel having an optical property which varies according to an applied signal.Type: GrantFiled: January 28, 2000Date of Patent: December 10, 2002Assignee: Donnelly CorporationInventors: Anoop Agrawal, Juan Carlos Lopez Tonazzi, Robert Steven LeCompte, Carl Baertelin, Douglas Alan Fischer