An aircraft fuselage includes an element forming a skin and a load-carrying structure supporting the element forming the skin. The load-carrying structure includes a plurality of elements forming a spar disposed parallel to an axial direction defined by the fuselage and a plurality of elements forming a frame disposed spaced apart along the axial direction. Each element forming a frame being arranged substantially perpendicularly to the elements forming a spar, where the element forming the skin is fastened on an external perimeter of each element forming a frame by means of fastening elements configured to keep the element forming the skin away from the external perimeter and where the element forming the skin is made of a transparent material.

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.

To prevent stress concentrations in the structure of an aircraft, an aircraft windshield assembly includes a peripheral frame, a windshield surrounded by the peripheral frame, the windshield comprising panes having respective lateral edges facing each other and respective other edges attached to the peripheral frame, and a pillar formed of at least one respective fishplate that covers the respective lateral edges facing each other and is bolted to the respective lateral edges facing each other, with no connection to the peripheral frame other than via the panes.

An article is provided. The article includes a first transparent conductive oxide layer, a transparent metal layer on the first transparent conductive oxide layer, wherein a thickness of the transparent metal layer continuously decreases in a direction; and a second transparent conductive oxide layer on the transparent metal layer.

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.

A system and method for sending signals at temperatures associated with hypersonic speeds. A window system in a hypersonic aircraft is provided. The window system comprises a transmissive window in an aeroshell of the hypersonic aircraft, a thermal seal, a sensor, and a sensor housing assembly enclosing the sensor. The transmissive window comprises a facesheet and insulating material adjacent to the facesheet. The thermal seal surrounds a perimeter of the facesheet and seals the facesheet to the aeroshell. The window system is radio-frequency transparent at temperatures associated with hypersonic speeds. The window system is configured to operate at an insertion loss of less than one decibel at the hypersonic speeds.

Disclosed herein is a panel assembly configured to form a mullion joint. The panel assembly can comprise a panel composed of a material substrate that, in some examples, can be transparent to radio frequency signals. The panel assembly can further comprise a first bezel configured to frame a perimeter of the panel on a first side of the panel. The panel assembly can comprise a second bezel configured to frame the perimeter of the panel on a second side of the panel opposite of the first side, the second bezel comprising cogs formed on a first edge of the second bezel. The cogs of the second bezel can be configured to receive and join with cogs of a bezel of a second panel assembly to form a mullion joint. The mullion joint can be transparent, opaque, or partially transparent to radio frequency signals and/or visible light.

A window with an emergency exit function for a helicopter is described that comprises: a frame shaped as a framework that can be coupled to a door of said helicopter provided with an opening; and a transparent element designed to engage the opening and held in position by the frame; the frame comprises a first side arranged abutting against the transparent element when a first force below a threshold value is exerted on the latter in a direction transversal to a first plane of a main portion of the transparent element, and which can be elastically moved away from the transparent element when the first force exerted on the latter exceeds the threshold value; and a second side having greater flexural rigidity than the first side in a second plane transversal to first plane and arranged abutting against the transparent element even when the force is greater than said threshold value.

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.

An electrically operated window shade system includes a frame that is mounted on the outer side of the inner wall of an aircraft cabin. A cassette is mounted in the frame and includes one or more motors and drive systems and one or two shade elements that are moved between raised and lowered positions under electric control. A user can operated the electric controls to adjust the amount of light coming through the window, as desired.