The invention relates to a method for manufacturing a composite aircraft window frame; the method comprises the steps of: a) positioning in a mold a preform made of pre-impregnated material including dispersed fibers, with a predefined orientation, in a thermosetting resin matrix; b) closing the mold so as to define a gap between at least one surface of said preform and a portion of said mold; c) injecting thermosetting resin into the closed mold through an inlet opening of the mold itself, so as to fill the gap and completely lap said surface of the preform; and d) applying a uniform hydrostatic pressure on the surface by the injection of the resin.

A transparency includes a plurality of sheets. Each sheet of the plurality of sheets can include a first major surface, an opposite second major surface, and a peripheral surface between the first major surface and the second major surface. The transparency can further include: an inter-sheet layer positioned between the first major surface of one of the sheets of the plurality of sheets and the second major surface of an adjacent sheet of the plurality of sheets; and a wireless sensor positioned in the inter-sheet layer. The wireless sensor includes a sensory portion configured to measure information representative of a condition of a portion of the transparency and a wireless transmitter configured to wirelessly transmit the received information to a wireless receiver.

A window assembly for use in a vehicle that includes a window frame including a first end and a second end opposite the first end, a first frictional slide track, a second frictional slide track, an opaque shade selectively movable within the first frictional slide track, and a transparent shade selectively movable within the second frictional slide track. The first frictional slide track and the second frictional slide track are positioned such that the opaque shade and the transparent shade are both selectively retractable within, and selectively extendable from, the first end of the window frame.

A window for an aircraft fuselage includes a transparent display for transmitting information to the passenger. The transparent display has a controllable data transmission circuit for varying the light transmission through pixels in the thin film transparent display. Natural light through the window acts as a backlight for the thin film transparent display.

A window operable to separate an interior from an exterior is disclosed. The window comprises a pressure pane and an anti-condensation assembly. The anti-condensation assembly is disposed in an interior direction relative the pressure pane. Further, the anti-condensation assembly comprises a substantially transparent substrate disposed in a spaced apart relationship relative the pressure pane. Additionally, the anti-condensation assembly comprises a resistively heatable layer associated with the first substrate. The resistively heatable layer is operable to generate heat when an electrical current is applied thereto. Accordingly, application of power to the resistively heatable layer may serve to reduce or eliminate the presence of visible condensation in the window.

An aircraft auxiliary display system for avoiding spatial disorientation includes a central processing unit (CPU), a sensing module, an activation display unit and an electro-optical visual unit. The CPU includes a storage unit and is electrically connected to the activation display unit. The sensing module is electrically connected to the CPU and includes a flight data sensing unit. The activation display unit is electrically connected to the electro-optical visual unit.

A window assembly heat transfer system is disclosed in which a window member has a selected transparency to monitored or sensed light wavelengths. One or more passages are provided in the window member for flowing a single-phase or two-phase heat transfer fluid, the passages being optically non-transparent to the monitored or sensed light wavelengths. A mechanism allows either evaporation or condensation of the fluid and/or balancing of a flow of the fluid within the passages. In one embodiment, the window assembly can be made by producing passages in a top surface of a first single plate, optionally producing passages in a bottom surface of a second single plate and bonding the top surface of the first plate to a bottom surface of a second single plate to form the window member with the passage or passages. In another embodiment, the window assembly can be made by providing a core around which the window member material is grown and thereafter removing the core to produce the passage or passages.

Methods, systems, and apparatuses are disclosed for conditioning or blending light for increasing the uniformity of light distribution and light wavelength customization, and light arrays integrated into structural and non-structural assemblies and sub-assemblies in cabin interiors.

Method, system and apparatus are provided for smart window activation to prevent laser disturbance. The apparatus may include a window formed of smart glass capable of being activated in discrete sections to be impenetrable to laser light and having a smart glass activation system. A sensor arrangement may detect laser light impacting on the window and may provide data as to the position of the impact on the window. A computer-implemented window protection system may receive input regarding detecting a laser beam impacting a window from the sensor arrangement, determine the position of the laser beam impact on the window and determine a section of the window in which the smart glass is to be activated, and control activation of the smart glass in the section of the window to make the section impenetrable to laser light by instructing the smart glass activation system.

Methods, systems, and apparatuses are disclosed for conditioning or blending light for increasing the uniformity of light distribution and light wavelength customization, and light arrays integrated into structural and non-structural assemblies and sub-assemblies in cabin interiors.