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.

A solar window shade for a window seat in an airliner for supplying electrical energy to charge a personal electronic device, including a window shade configured to cover a window, a solar panel attached to an outside face of the window shade, the solar panel facing outward to receive light from outside a passenger cabin, and a charging port incorporated into the window shade, the charging port electrically connected to the solar panel.

A coated transparency includes: a transparency; a base layer on the transparency, the base layer comprising at least one selected from an organic compound, an organosilicon compound, and a polysiloxane compound; a metal layer physically contacting the base layer; and a metal oxide layer on the metal layer, the metal oxide layer comprising aluminum doped zinc oxide (AZO).

A holder apparatus for holding an object relative to an airplane cabin window frame can include a structure that locates in opposing window shade channels of the frame, and at least one tray pivotably mounted relative to the structure. A system for holding an object relative to an airplane cabin window can include a holder apparatus with a structure that engages a window frame of the window, and at least one tray pivotably mounted relative to the structure. The structure can engage opposing window shade channels of the window frame in response to rotational displacement of the structure relative to the frame. A method for installing an apparatus in a window can include placing the apparatus between channels of the window, rotating and engaging ends of the apparatus with the window frame channels and displacing it to the bottom of the frame.

According to an embodiment, an electrically switchable mirror includes: a first electrically switchable layer of cholesteric liquid crystal material, the first electrically switchable layer having a first state in which right-handed circularly polarized light incident thereon is reflected and left-handed circularly polarized light incident thereon is transmitted and a second state wherein right-handed and left-handed circularly polarized light incident thereon are transmitted; a second electrically switchable layer of cholesteric liquid crystal material, the second electrically switchable layer having a first state in which left-handed circularly polarized light incident thereon is reflected and right-handed circularly polarized light incident thereon is transmitted and a second state wherein right-handed and left-handed circularly polarized light incident thereon are transmitted; and a first electrically switchable wave plate disposed between the first and second electrically switchable layers.

An aircraft transparency assembly includes an aircraft transparency having at least one ply having an outer surface and an extended portion. The assembly also includes a pressure seal configured to engage the extended portion of the ply, wherein the pressure seal includes a pressure seal body and at least one integrated compression stop. The transparency assembly can also include an anti-static drain assembly including at least one flexible conductive element having a first end in electrical contact with the outer surface of the ply, for example with an optional conductive coating on the outer surface of the ply, and a second end configured to contact the pressure seal.

A windshield wiper system for use on an aircraft includes a controller and a wiper assembly including a wiper arm, a wiper blade, and a moving block. Further, the windshield wiper system includes a rail assembly including a rail assembly rack, a plurality of electromagnets, and an electrical interface. The electrical interface and the plurality of electromagnets induce a force on the moving block of the wiper assembly, causing the wiper assembly to sweep across the windshield of the aircraft. The controller is coupled to the rail assembly and the controller is configured to direct the motion of the wiper assembly through command signals to the rail assembly.

A window installation includes a phase-change filler material sealing an outer edge of the window, and coupling the window to a frame around the window. The filler material in a solid state rigidly holds the window in place. When the filler material is in a liquid state it allows the window to float in its coupling to the frame. There may be supports within the rigid material that contact the window, but allow the window to expand or contract by sliding along the supports. The installation may be useful in situations where the window is subjected to thermal shocks, or other sorts of heating. The installation may be used for a sensor window, and may be part of a hypersonic vehicle.

In one embodiment, an apparatus includes a collapsible workstation assembly to be used in a temporarily-mounted control system of an aircraft. The collapsible workstation assembly is mounted to a floor of the aircraft via one or more mounting plates and one or more adaptive floor plates. The collapsible workstation assembly includes a number of modules for display and user controls. Each of the modules are connected via hinges and hinge locks to be moved between a deployed position for use and a stowed position when not in use. The collapsible workstation assembly is further connected to an observer chair assembly and a temporary door plug.

An inflatable life raft system for an aircraft includes a window coupled to a fuselage portion of the aircraft. A mechanism is used to selectively detach the window from the fuselage. An inflatable life raft is deployable to the exterior of the aircraft upon detachment of the window from the aircraft.