Abstract: A sensor-cluster apparatus, in which a sensor configured to detect and collect external environment information is mounted in a case. The sensor-cluster apparatus includes a body member on which one kind or more of sensors are mounted on one surface thereof, a case in which an inner space is provided, and one surface thereof is opened to define an opening and on which the body member is mounted so that each of the sensors is exposed to the opening, and a position control device mounted inside the case to adjust a mounting position or a mounting angle of the body member.

Abstract: Methods and systems for controlling an aircraft cabin display are described herein. The method comprises obtaining a reflected color on a surface adjacent to a cabin window of an aircraft, generating an image having an image color in accordance with the reflected color on the surface adjacent to the cabin window, and displaying the image having the image color on a display device covering the cabin window.

Abstract: An aircraft fuselage includes a structure, considered in respect of all or part of the fuselage, with fuselage upper sub-structure constituting an upper part of the fuselage and a fuselage bottom sub-structure constituting a lower part of the fuselage. Openings in the structure of the fuselage are intended for the installation of windows or doors for exiting the fuselage. Furthermore, the fuselage upper sub-structure and the fuselage bottom sub-structure form fuselage sub-structures that are assembled with one another via at least one lintel in which all or some of the openings intended for installing the exit doors or windows are formed.

Abstract: A fastener includes a head that is configured to be engaged by a tool, and a shaft extending from the head. The shaft includes a distal end that is opposite from the head. At least one optical component is coupled to one or both of the head or the shaft. The optical component(s) is configured to allow light to pass through the fastener. A window system includes a panel that includes an exterior surface and an interior surface, and the fastener extending between the exterior surface and the interior surface of the panel. A screen is coupled to the interior surface. The screen receives light from the optical component(s) of the fastener.

Abstract: A site monitoring system (SMS) may analyze information from one or more sites to determine when a device, a sensor, a controller, or other structure or component associated with a network of optically switchable devices has a problem. The system may, if appropriate, act on the problem. In certain embodiments, the system learns customer/user preferences and adapts its control logic to meet the customer's goals. In various embodiments, the system updates a memory component associated with one or more optically switchable windows and/or controllers. The memory component may be updated to reflect an updated control algorithm and/or associated parameters in some cases.

Abstract: A method and system for an electrically switchable window system for an aerospace vehicle. The electrically switchable window system comprises electrically switchable windows and a window controller system connected to the electrically switchable windows. The window controller system receives a group of wireless signals from an onboard network system that controls systems in the aerospace vehicle and changes voltages applied to the electrically switchable windows when the group of wireless signals are received. The changes in the voltages change an amount of light passing through the electrically switchable windows.

Abstract: A latch system includes an actuation module having first and second actuation mechanisms. The first actuation mechanism includes a first handle, a lock tab and an inner rod coupled together. The second actuation mechanism includes at least one second handle, a conversion block and an outer rod coupled together with the outer rod and the conversion block each having a slot. At least one latch module has a retractable latch. A control cable connects the conversion block and the latch module such that rotation of the conversion block in a first direction retracts the latch. A lock is operably engagable with the lock tab to selectively allow and prevent rotation of the inner rod. Rotation of the inner rod in the first direction rotates the conversion block. Rotation of the outer rod in the first direction rotates the conversion block without rotating the inner rod.

Abstract: A latch system includes an actuation module having first and second actuation mechanisms. The first actuation mechanism includes a first handle coupled to a locking rod having an end slot and an oppositely disposed rod insert. The second actuation mechanism includes at least one second handle, a conversion block and an outer rod coupled together. The outer rod has an open end and a slot. At least one latch module has a retractable latch. A control cable connects the conversion block and the latch module such that rotation of the conversion block in a first direction retracts the latch. A lock is operably engagable with the end slot to selectively allow and prevent rotation of the inner rod. Selective rotation of the locking rod in the first direction rotates the conversion block. Rotation of the outer rod in the first direction rotates the conversion block without rotating the locking rod.

Abstract: An insulated pipe includes an elongated tube having a first end, a second end, and a sidewall extending therebetween, including an inner surface and an outer surface. The insulated pipe also includes an insulating member covering a portion of the outer surface of the sidewall and a planar moisture sensor. The planar moisture sensor is positioned in the insulating member or between the insulating member and the outer surface of the tube sidewall. The planar moisture sensor includes: a first electrode having a flat conductive member having an inner surface and an outer surface; a second electrode spaced apart from the first electrode having a flat conductive member having an inner surface and an outer surface, and a dielectric layer. The dielectric layer includes an absorbent dielectric polymer material positioned between and in electrical contact with the inner surfaces of the first electrode and the second electrode.

Abstract: The present invention relates to an amphibious vehicle comprising a vehicle frame and a cab supported by said vehicle frame, said cab being connected to said vehicle frame via hinge means so as to allow tilting of said cab about said hinge means between a closed position and an open position, wherein said vehicle comprises a sealing arrangement comprising sealing means arranged to provide liquid tight sealing between the cab and the vehicle frame in said closed position, wherein in the closed position, the sealing arrangement is arranged to provide a confined space for protecting components of said vehicle enclosed inside said space.

Abstract: Adjustment mechanisms, systems and methods allow for a moveable aerodynamic surface to be positionally adjusted relative to a stationary adjustment surface so as to ensure smooth aerodynamic transition between such surfaces. The adjustment mechanisms may include a base structure adapted for fixed connection to the moveable aerodynamic surface, a fixed-position receiver opposing the base structure and adapted for positionally fixed connection to the support structure of the moveable aerodynamic surface and an adjustment bolt having a head and a threaded shaft extending from the head through an elongate slot of the base structure, the slot defining an elongate axis which is aligned with an adjustment axis for the moveable aerodynamic surface, and being threadably coupled to the receiver to operably interconnect the base structure and the receiver.

Abstract: A window assembly for an aircraft includes a window frame being arranged bordering a window opening in a hull of the aircraft, a window seal being attached to the window frame, a window being supported by the window frame and sealed to the window frame by the window seal, a window retainer covering the window seal and the window frame from the inside of the aircraft, and a transparent vapor barrier being supported by the window retainer and covering the window from the inside of the aircraft such that an air gap is formed between the window and the transparent vapor barrier.

Abstract: An aircraft includes a fuselage defining a mold line, at least one frame disposed in the fuselage, at least one transparent pane suspended within the frame. The transparent pane is a deformable material that defines a first surface position h1 when not subjected to a differential pressure ?P thereacross and a second surface position h2 when subject to the differential pressure ?P thereacross. The first and second surface positions are defined with reference to the outside mold line. The first surface position h1 defines a reverse curvature. In response to the differential pressure ?P, the second surface position h2 includes bulging of the transparent pane by a predetermined distance ?h. The frame is constructed to be positioned within the aircraft such that the transparent pane presents a surface, when subjected to the pressure differential ?P, that is substantially consistent with the outside mold line of the vehicle.

Abstract: An aircraft window includes an outer window assembly that includes a pressure pane coupled to a pressure pane frame. An inner window assembly includes a bezel adapted to couple to a perimeter of the inner window assembly against the outer window assembly. The bezel has a plurality of attachment features disposed thereon. A plurality of retaining features is disposed around the perimeter of the window. The retention features are configured to engage the attachment features for retaining the inner window assembly on the outer window assembly.

Abstract: A system. The system may include at least one monitor mounted on a wall panel. The wall panel may be within an interior of an aircraft. Each of the at least one monitor may be configured to mimic an aircraft window. Each of the at least one monitor may include a shade feature.

Abstract: Tintable optical components such as windows are provided with a controller designed or configured to control the tinting in a manner that resists exposure to damaging thermal shock. The controller determines that a trigger condition for thermal shock is occurring or is about to occur and takes steps to avoid damaging thermal shock. In some cases, these steps include increasing the transmissivity of the optical component or holding the component in a highly transmissive state. In some cases, the steps involve heating the component.

Abstract: A system and method for displaying the external environment of the airplane. The system includes a camera mounted on the door of the airplane. The camera having lens for capturing the external environment illuminated by a illumination source in order to provide a video signal, and at least one display screen connected with the camera for receiving the video signal.

Abstract: A vehicle is disclosed that includes systems for adjusting the transmittance of one or more windows of the vehicle. The vehicle may include a camera outputting images taken of an occupant within the vehicle. The vehicle may also include an artificial neural network running on computer hardware carried on-board the vehicle. The artificial neural network may be trained to classify the occupant of the vehicle using the images captured by the camera as input. The vehicle may further include a controller controlling transmittance of the one or more windows based on classifications made by the artificial neural network. For example, if the artificial neural network classifies the occupant as squinting or shading his or her eyes with a hand, the controller may reduce the transmittance of a windshield, side window, or some combination thereof.

Abstract: A window frame assembly for an aircraft, includes a window frame of composite material, adapted for attachment in a window opening of an aircraft, having an outer flange with an exterior surface and an interior surface, a metal erosion shield attached to the exterior surface of the outer flange, and a polymer adapter ring, attached to the interior surface of the outer flange. The window frame has a substantially constant thickness, and the erosion shield has a substantially constant cross-sectional shape. The adapter ring has a sloped engagement surface configured for supporting a window pane assembly.

Abstract: A porthole, a porthole plug in a vehicle, and an aircraft with portholes are provided. The porthole includes an opaque plug with an aperture therethrough. A camera is arranged with a lens aligned with the aperture.

Abstract: 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.

Abstract: A vehicle includes a windshield having an integral pressure sensor. A signal from the pressure sensor is used to identify an impact against the windshield as a stone impact. Responsive to identifying the stone impact, identifying any large truck located within a predetermined radius of the vehicle. Responsive to identifying a large truck, the vehicle is directed to make an evasive maneuver to avoid stones dropped or thrown by the large truck.

Abstract: A fiber composite component made of a fiber composite material comprises at least one first surface section, at least one second surface section and at least one transition region. The first surface section and the second surface section are arranged at an angle to each other and incorporate the transition region. The transition region comprises at least one first curvature section and at least one second curvature section whose mean curvatures differ from each other, which curvature sections connect to each other in a tangentially continuous manner. The first surface section connects to the transition region, and the transition region connects to the second surface section in each case in a tangentially continuous manner. In one example, the radius of curvature of the first curvature section is smaller than that of the second curvature section.

Abstract: 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 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.

Abstract: Window units, for example insulating glass units (IGU's), that have at least two panes, each pane having an electrochromic device thereon, are described. Two optical state devices on each pane of a dual-pane window unit provide window units having four optical states. Window units described allow the end user a greater choice of how much light is transmitted through the electrochromic window. Also, by using two or more window panes, each with its own electrochromic device, registered in a window unit, visual defects in any of the individual devices are negated by virtue of the extremely small likelihood that any of the visual defects will align perfectly and thus be observable to the user.

Abstract: 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.

Abstract: A structure may comprise a first outer layer and a polymer fiber composite layer mounted on one side of the first outer layer.

Abstract: A thermal barrier apparatus for a window system includes a closed curve-shaped plate having a plurality of concentric channels, a plurality of walls each defining adjacent concentric channels, each of the walls including a plurality of openings between adjacent concentric channels, an outer wall formed on an outer peripheral edge of the closed curve-shaped plate, the outer wall including a plurality of openings, and an inner wall formed on an inner peripheral edge of the closed curve-shaped plate including a plurality of openings. The plurality of openings and concentric channels are configured to provide an air flow path for conduction of air through the thermal barrier apparatus to an exterior of the thermal barrier apparatus.

Abstract: 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.

Abstract: An emergency exit arrangement for a vehicle and or a building comprising of a plurality of spring pressured stud assembly having a plurality of locking pin in the upper region connected correspondingly to a plurality of rope which is connected to a first pulling device; a plurality of locking pin in the lower region connected correspondingly to a plurality of rope which is connected to a second pulling device. Sequential pulling of the first and the second pulling device ejects out the aperture cover. The pulling devices are electrical, operated by pressing a button; or through temperature sensor, impact sensor, pressure sensor, smoke sensor and or a combination thereof. The pulling devices are alternatively rotatable knobs. The aperture cover is easily mountable.

Abstract: The invention refers to a composite structure for an aircraft comprising a panel and at least one stringer joined to a surface of the skin panel, the stringer having a foot and a web protruding from the foot, and a run-out section at one of its ends. The panel includes a plurality of stacked and co-cured plies of composite material, and at least part of the foot of the stringer at the run-out section, is inserted between two plies of the panel, and it is co-bonded, co-cured or secondary bonded with said two plies. The structure of the invention provides a reinforced join between the foot of the stringer and the skin panel, avoiding peeling or de-bonding problems, without substantially modifying the manufacturing process.

Abstract: A window system for a platform comprising a window pane, a retention frame, and a biasing system. The window pane may be configured to contact a sealing system. The retention frame may be configured to contact the sealing system and hold the window pane against the support frame. The biasing system may be configured to bias the retention frame toward the support frame while the support frame and the retention frame are in a configuration that holds the window pane. Removal of the biasing system may cause the retention frame and the window pane to be removable.

Abstract: A method of forming cutouts in an aircraft fuselage may include forming a first cutout and a second cutout in side-by-side relation to one another in a side region of the fuselage. The method may further include configuring the first cutout and the second cutout such that a direct load path extends along the side region substantially continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region generally over the second cutout.

Abstract: 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.

Abstract: A jettisonable door system for an aircraft includes an upper hinge having a forward portion that is hingedly coupled to an airframe of the aircraft, the upper hinge having an aft portion that is releasably secured to an upper outboard plate with an upper pin. The jettisonable door system further includes a lower hinge having a forward portion that is hingedly coupled to the airframe of the aircraft, the upper hinge having an aft portion that is releasably secured to a lower outboard plate with a lower pin. A rotation of the upper pin releases the upper hinge from the upper outboard plate and a rotation of the lower pin releases the lower hinge from the lower outboard plate.

Abstract: A method of installing a door in an access opening in a skin of an aircraft. A composite inner door panel is positioned against an inside face of the skin. A composite outer door panel is positioned against an outside face of the skin. A plurality of fasteners is installed through fastener openings in the composite outer door panel. The plurality of fasteners is tightened to form a chamfered interface between the skin and the composite outer door panel.

Abstract: A fastening assembly for a window of a pressurized fuselage of an aircraft includes a fastener received through a mounting hole defined in the window, an edge attachment member fixing the window to the fuselage, and a bushing assembly embedded in the mounting hole. The bushing assembly includes an inner sleeve bushing radially interposed between the fastener and the window and an outer sleeve bushing radially interposed between the inner sleeve bushing and the window. The inner sleeve bushing is formed from relatively less rigid metal compared with metal of the fastener and the outer sleeve bushing is formed from relatively rigid metal compared with material of the window and the metal of the inner sleeve bushing.

Abstract: Fiber reinforced composite structures having curved stepped surfaces are fabricated by laying up plies of fiber reinforced material over a tool having a stepped tool feature. The plies are rotated about a fixed axis as they are laid up to substantially form a fixed axis rosette pattern. The plies are angularly oriented such that at least certain of the plies have fiber orientations other than 0, +45, ?45 and 90 degrees. Potential bridging of the fibers over the stepped tool features is reduced or eliminated by cutting slits in the plies in the area of the stepped features, so that the plies can be fully compacted.

Abstract: 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 capacitively coupling the window pane to the fuselage after the frequency of the electromagnetic energy reflected by the window pane exceeds approximately 1 GHz.

Abstract: A window system for a vehicle comprising a pressure and thermal window pane, a seal system, and a retainer system. The pressure and thermal window pane may be configured to provide desired pressure protection and desired thermal protection when exposed to an environment around the vehicle during operation of the vehicle. The pressure and thermal window pane may have a desired ductility. The seal system may be configured to contact the pressure and thermal window pane to seal the pressure and thermal window pane. The retainer system may be configured to hold the seal system and the pressure and thermal window pane.

Abstract: 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.

Abstract: An electromagnetic shield mesh 25 is provided on a window part 21, and a gasket seal 50 is provided between the electromagnetic shield mesh 25 and a window frame 30 made of a conductive material. The first seal part 51 of the gasket seal 50 has a low volume resistivity, and makes it possible to prevent electromagnetic noise from entering the inside of an airframe between the window part 21 and a window frame 30. Moreover, the second seal part 52 of the gasket seal 50, which is made in contact with the electromagnetic shield mesh 25 of the window part 21 on the outer perimeter side of window panels 23A and 23B, has a volume resistivity of, for example, 300 ?cm or more, so that it becomes possible to prevent corrosion from occurring at contact portions with a clamp 28, a clip 29 or the like.

Abstract: An electrical system responsive to overheating and/or electric arcing of an electrically conductive member, e.g. a heating member of an aircraft windshield, includes a first switch in a first current path, and a second switch in a second current path. The first current path is from an electrical power supply through the first switch, through an arc sensor to the heating member to the power supply. The second current path is from a temperature sensor monitoring the temperature of the heating member through the second switch to a temperature controller. When the temperature of the heating member is at or above a predetermined value, the temperature controller causes the first switch to open. When there is arcing, the second switch is moved to the open position. The temperature controller senses that the second switch is open and causes the first switch to open.

Abstract: This disclosure describes system and methods for creating an autonomous electrochromic assembly, and systems and methods for use of the autonomous electrochromic assembly in combination with a window. Embodiments described herein include an electrochromic assembly that has an electrochromic device, an energy storage device, an energy collection device, and an electrochromic controller device. These devices may be combined into a unitary electrochromic insert assembly. The electrochromic assembly may have the capability of generating power sufficient to operate and control an electrochromic device. This control may occur through the application of a voltage to an electrochromic device to change its opacity state. The electrochromic assembly may be used in combination with a window.

Abstract: 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.

Abstract: A three dimensional woven preform, a fiber reinforced composite incorporating the preform, and methods of making thereof are disclosed. The woven preform includes one or more layers of a warp steered fabric. A portion of the warp steered fabric is compressed into a mold to form an upstanding leg. The preform includes the upstanding leg and a joggle in a body portion. The body portion and upstanding leg are integrally woven so there is continuous fiber across the preform. A portion of the warp steered fabric includes stretch broken carbon fibers in the warp direction, and another portion includes conventional carbon fibers. The warp steered fabric can be woven on a loom equipped with a differential take-up mechanism. The warp steered fabric can be a single or multilayer fabric. The preform or the composite can be a portion of an aircraft window frame.

Abstract: 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.

Abstract: 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.

Abstract: The present invention provides poly(ureaurethane)s including a reaction product of components comprising: (a) at least one isocyanate functional ureaurethane prepolymer comprising the reaction product of: (1) at least one isocyanate functional urethane prepolymer comprising the reaction product of: (i) a first amount of at least one polyisocyanate; and (ii) a first amount of at least one branched polyol; and (2) water, to form an isocyanate functional ureaurethane prepolymer; and (b) a second amount of at least one polyisocyanate and a second amount of at least one branched polyol; compositions, coatings and articles made therefrom and methods of making the same.

Abstract: The invention relates to a device for fastening systems in an aircraft. It comprises on the one hand a ring-shaped base (2) and on the other hand arms (4, 6) borne by the ring-shaped base (2), extending outward from the latter and bearing systems supports.