Abstract: 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.

Abstract: A passenger cabin window, especially in a commercial passenger transport aircraft, includes an outer window pane and an inner window pane with an interspace formed therebetween, and a frame around the perimeter of the window interspace. The frame has a funnel-like shape that expands or enlarges from the smaller dimensions of the outerpane to the larger dimensions of the inner pane. At least a visible portion of the frame bounding the window interspace is provided with a mirror reflective surface and particularly a reflective coating thereon. The reflective surface reflects the outside scene, so that the window frame with the reflective surface appears to be a part of the outside view, to a passenger looking out of the window. This visually enlarges the window opening and visually reduces the structural thickness of the fuselage wall, thereby avoiding a closed-in feeling and a tunnel-vision-effect through the window funnel.

Abstract: 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. The first and second lenses may have the same dimensions and/or be rectangular in shape. The first lens may have a length of at least 40 inches, a width of at least 30 inches, and an area of at least 1200 square inches. The shade may be pleated, tubular in shape, and have means for maintaining the horizontal alignment of the shade rail.

Abstract: A portable defogging device for defogging multi-paned windows comprising an open loop source of low moisture gas and a flexible conduit for introducing the gas into the enclosed space between the window panes. A regulator is used to introduce the fixed rate of flow of gas through the flexible conduit and into the enclosed space so as to remove the pre-existing or previous condensation in the enclosed space. In a double-paned aircraft window, the low moisture gas is introduced through a pressure equalization hole in the window. A method of defogging a multi-paned window comprising passing a low moisture gas through a flexible conduit and into an enclosed space between at least two window panes. The discharge of gas is regulated to a constant flow so as to remove moisture from the enclosed space, wherein the defogging device is deactivated and removed from the window to complete the defogging cycle.

Abstract: 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 cur

Abstract: The present invention is embodied in a polyurethane composition suitable for coating, casting or laminating, which incorporates a prescribed additive selected to increase the composition's electrical conductivity without adversely affecting the composition's transparency and percent haze and without adversely affecting its adhesion to an underlying substrate or its environmental durability, especially with regard to humidity resistance. The prescribed additive is an ionizable metal salt of a perfluoroalkylsulfonimide, in a weight percent of 0.5 to 5.0, with the metal being an alkali metal and the preferred perfluoroalkylsulfonimide being trifluoromethanesulfonimide. The most preferred salt is lithium trifluoromethanesulfonimide. The preferred polyurethane include both aliphatic polyetherurethanes and aliphatic polyesterurethanes.

Abstract: 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.

Abstract: The invention is relative to a window frame, in particular a window for a helicopter intended to fix the window onto a support. This frame includes cutting out means driven by pulling on at least a part of the window perimeter in order to divide into two at least a section of the frame and thus detach the window from the support.

Abstract: A countermeasure device for the in-band frequency agile laser threat posed to the eyes of operator(s) comprises a rotating shutter operating at a predetermined speed and with alternating clear and nearly opaque sectors. The shutter is designed to spin in front of the operator's field of vision at a rate sufficient to avid a flickering image. The device significantly increases operator protection from an initial laser pulse over existing devices while allowing sufficient ambient light to reach the retina for clear vision. This device will eliminate dazzling which interferes with operator's ability to pinpoint the location of the laser source for neutralization. The device also eliminates the occurrence of damage to both eyes simultaneously.

Abstract: An automatic-shutter system functions as a counter-measure to the in-band frequency agile laser threat posed to the eyes of pilot(s)/operator(s). Ideally it is desirable to protect the operator from every laser pulse including the first. However, the lack of fast shutters or optical gates (faster than a micro-second) suitable for visible usage has prevented the protection from a first pulse threat. The automatic-shutter system detects the first pulse and provides protection against any subsequent pulses. This is achieved by a multi-directional detector system for actuating shutters on the aircraft/vehicle. The detector, after detecting a pulse of laser light, further comprises processing means in electrical communication with the multi-directional detector for processing a detected pulse of laser light and to generate a signal responsive thereto. A plurality of shutters can be individually or group dropped in response to shutter actuating means to provide protection against subsequent pulses of laser light.

Abstract: A passenger cabin window, especially in a commercial passenger transport aircraft, includes an outer window pane and an inner window pane with an interspace formed therebetween, and a frame around the perimeter of the window interspace. The frame has a funnel-like shape that expands or enlarges from the smaller dimensions of the outer pane to the larger dimensions of the inner pane. At least a visible portion of the frame bounding the window interspace is provided with a mirror reflective surface and particularly a reflective coating thereon. The reflective surface reflects the outside scene, so that the window frame with the reflective surface appears to be a part of the outside view, to a passenger looking out of the window. This visually enlarges the window opening and visually reduces the structural thickness of the fuselage wall, thereby avoiding a closed-in feeling and a tunnel-vision-effect through the window funnel.

Abstract: The invention relates to a window unit W for aircraft cabins, comprising an outer window frame 1, an inner window frame 3, a window pane 2 lying between them, and possibly having a sun-visor 4, a roller blind 34 or the like arranged between the inner window frame 3 and a possible covering frame 5, the window unit W being insertable into the opening 7 in a side-wall panel 6 or the like in the aircraft cabin. In order to make it possible for the window unit W to be rapidly and simply installed and removed, the invention makes provision for the window unit W to have a centering device and at least two snap fastenings 13, advantageously with locking devices, to detachably connect it to the side-wall panel 6, or to components connected thereto, the side-wall panel 6, or components connected thereto, having any necessary mating parts for the centering device for the snap fastenings 13.

Abstract: A missile includes a fuselage with a roll axis and a nod axis perpendicular to the roll axis, and a conformal window mounted to a forward-facing end of the fuselage. There is a sensor system with a field of regard through the window and a line of sight, and a sensor system pointing mechanism affixed to the airframe and upon which the sensor system is supported. The sensor system pointing mechanism includes a gimbal structure having a first degree of rotational freedom about the roll axis and a second degree of rotational freedom about the nod axis, and a linear translational mechanism connected to the sensor system. The linear translational mechanism is operable to translate the sensor system away from the window with increasing angular deviation of the line of sight of the sensor system from the roll axis. Preferably, the translational mechanism is a slider-crank mechanism.

Abstract: A double pane window for an aircraft cabin has a passive air dehumidifying channel (5, 5A) that is in heat exchange contact with a window metal frame (1) which is in turn in heat exchange contact with the atmosphere outside the aircraft. The air dehumidifying channel (5, 5A) communicates through a first air flow port (6) with the cabin space and through a second air flow port (7) with a space enclosed between the double panes.