A laminated glazing unit includes at least one first sheet of glass and one second sheet of glass glued to one another via a first adhesive interlayer, the first sheet of glass being intended to constitute the surface of the laminated glazing unit in contact with the outside atmosphere, in which the laminated glazing unit further includes, between the first sheet of glass and the second sheet of glass, an LOC (Localizer) antenna receiving between 100 and 120 MHz and a GLIDE (Slope) antenna receiving between 320 and 340 MHz, each antenna having dimensions that are sufficiently small not to hamper the vision, even to be practically invisible through the laminated glazing unit.

A network system for monitoring and storing data of aircraft intelligent windows or windshields to provide useable life of, provide real life performance of, and/or measure characteristics and/or properties of, the windshields forwards the data from sensors mounting the windshield to a window sensing hub having a microprocessor programed to receive and process the data to determine the performance of the windshield and formatting the data in accordance to a preset program, wherein the program includes providing data from the sensors that measures characteristics and properties of the windshield that are active during the period in which the data is taken. An aircraft central maintenance system connected to the window sensing hub receives the formatted information from the window sensing hub and unfiltered or unformatted information, wherein the unfiltered information from the windshield is acted on by the central maintenance system to provide an estimated useable life of the windshield.

A method for constructing at least two fleets of aircraft of different families for which each aircraft has a front part comprising windows, a framing of the windows and a windshield front fairing, comprising, for each aircraft, constructing a module composed of the framing of all of the windows allowing outward visibility from the cockpit and of the windshield front fairing whose form is identical and constant for all the aircraft of the fleets and independent of a form of the fuselages thereof, and constructing a section of fuselage of which at least a part of an edge of the fuselage is of a form identical to an edge of the module, such that the module can be assembled directly with the contiguous fuselage section, whatever the aircraft of the fleets.

A canopy for an aircraft includes a pivot assembly including a first hinge and a second hinge opposite from the first hinge. The first hinge includes a first pivot slot having a first length. The first pivot slot is configured to retain a first aft pin of a fuselage of the aircraft. The second hinge includes a second pivot slot having a second length. The second pivot slot is configured to retain a second aft pin of the fuselage of the aircraft. The first length differs from the second length.

A pane assembly (2) for a window (8) arranged in the outer wall (4) of an aircraft (6) in a window plane (10) contains a transparent cover pane (12) in a cover plane (14), a switching film (16) in a scattering plane (18), which is switchable between a transparent state (ZT) and a diffuse state (ZD), a luminous film (20) in a light plane (22) having LEDs (24), wherein a spacing (A) between each two LEDs (24) in relation to one another is at least five times their transverse extension (Q), wherein the pane assembly (2) is arranged in front of the window (8) in an installed state (M), so that scattering plane (18), light plane (22), and window plane (10) extend in parallel to one another and the luminous film (20) is arranged between the window (8) and the switching film (16), and window (8), switching film (16), and luminous film (20) are located aligned one behind another on the line of sight (26).

A window assembly (40) contains the window (8) and the pane assembly (2) arranged in front of it in the installed state (M).

A window pane includes at least one structural substrate referred to as interior substrate, intended to face toward a host structure within which the window pane is intended to be fixed, and having a face, referred to as interior face, wherein the interior face of the substrate includes, projecting therefrom and at the edge or near the edge and along at least one of the sides of the window pane, at least one male or female retaining element intended to collaborate with at least one respectively female or male retaining shape arranged in the host structure of the window pane.

A sidewall assembly for an aircraft and an aircraft are provided. In one example, the sidewall assembly includes a window. A sidewall portion has an inner-facing side and at least partially surrounds the window. The sidewall portion and the window have a curved contour. A transparent display panel is coupled to the sidewall portion and covers the inner-facing side of the sidewall portion including the window. The transparent display panel includes a display screen configured to display information to a passenger. The transparent display panel including the display screen have a curved contour that substantially matches the curved contour of the sidewall portion and the window. A display controller is in communication with the transparent display panel to communicate a video/audio signal providing the information to the display screen.

A method of improving optical characteristics of an optical window operating in a flow of fluid and having first and second panes of optically transmissive material—each having an edge adjacent to, parallel with, and at least partially coextensive with each other—is described herein. The method includes inserting a thermally conductive blade between two adjacent edges of the first and second panes of optically transmissive material; and lifting an adverse flow stagnation zone forward of the optical window by protruding the thermally conductive blade into the flow of fluid from an outer surface of the panes of the optical window.

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.

A windshield assembly (110) comprises a support panel (102), a windshield (112), and a frame (140), surrounding the windshield (112). The frame comprises a frame inboard leg (142), which is in contact with an inboard windshield surface (114). A hinge (160) pivotally couples a frame-inboard-leg top portion (148) of the frame inboard leg (142) to the support panel (102) and has a pivot axis. A channel (161) is provided in the support panel (102). At least a portion of the frame-inboard-leg bottom portion (150), at least a portion of the frame-inboard-leg first lateral portion (152), and at least a portion of the frame-inboard-leg second lateral portion (154) are located in the channel (161). The channel (161) comprises a channel base leg (162). A seal (180) is located in the channel (161) between the channel base leg (162) and the frame inboard leg (142).