A system includes a robotic arm, a rotisserie control linkage, and a computer system. The robotic arm includes a touch probe and laser head. The rotisserie control linkage is configured to couple to a transport cart. The computer system is communicatively coupled to the robotic arm and the rotisserie control linkage and is configured to control the system to probe, using the touch probe of the robotic arm, a transparent outer layer of an aircraft canopy located on the transport cart in order to determine surface measurements of the aircraft canopy. The computer system also controls the system to ablate, using a plurality of predetermined parameters and the laser head of the robotic arm, an interface layer located between the transparent outer layer and the aircraft canopy, wherein movements of the robotic arm during the ablation are based on the surface measurements.

An approach to seeker windows for aircraft comprises a window layer comprising an IR transparent material, the window layer comprising a first side and a second side substantially opposite the first side; and a heating layer on the first side or the second side of the window layer, the heating layer configured to apply a heating profile to the window layer to reduce thermal shock imparted to the window layer when the seeker window is exposed to hypersonic flight conditions.

The present disclosure is directed to a blended wing body aircraft including a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and a main body along a leading edge of the aircraft; a cabin located within the main body and a transitional portion of the blended wing body; and a plurality of transparent panels in a ceiling of the cabin configured to transmit light from outside the blended wing body aircraft to inside the cabin.

Aircraft window assemblies and methods. The aircraft window assemblies comprise a window frame configured to support a window pane on an aircraft skin about a window aperture defined in an aircraft skin. The window frame includes a base formed of a continuous fiber reinforced thermoplastic composite and at least one overmolded feature molded to the base. The base defines a central aperture and includes circumferential flange portion configured to support the base on the aircraft skin surrounding the window aperture and a skirt portion extending inwardly from the circumferential flange portion and surrounding the central aperture. The skirt portion is non-planar with the circumferential flange portion and comprises a support surface for the window pane. The methods comprise forming the window frame, which comprises stamp-forming the base of the window frame from a continuous fiber reinforced thermoplastic composite sheet and overmolding the at least one overmolded feature to the base.

A window unit for an aircraft includes a wall module having a side wall laterally delimiting an aircraft cabin. The side wall has a window opening and the wall module has retaining portions. A window module has a window frame accommodating at least one windowpane and the window module has fastening portions. A fastening configuration fastens the window module on the side wall in a region of the window opening. The fastening configuration is formed by a respective fastening portion engaging with a respective retaining portion. The retaining portions and the fastening portions are movable into a plug-in position by a plug-in movement of the window module and are movable from the plug-in position into a securing position by a rotary movement of the window module. The wall module and the window module are interconnected by a form-locking connection in the securing position.

A light aerial vehicle laminated glazing includes a structural transparent plastic sheet covering the whole of the surface of the glazing, a protective transparent plastic sheet covering the whole of the surface of the glazing, an interlayer adhesive bonding the structural and protective sheets, a glass covered with a conductive layer having a heating function incorporated within the adhesive and covering a fraction of the surface of the glazing at most equal to 66% containing the main viewing zone.

A method, comprising: providing a light source, a high contrast providing object, and an image acquisition device; emitting a light beam from the light source through the high contrast providing object, a transparent object and a surface of the transparent object toward the image acquisition device; exposing the surface of the transparent object to icing conditions such that a layer of ice is formed by ice accretion on the surface, wherein the light beam traverses the layer of ice after having traversed the transparent object; acquiring a series of images over time of the high contrast providing object using the image acquisition device; determining blur occurring in the series of images over the time; and quantifying the loss of visibility over the time through the transparent object on the basis of the determined blur.

A system for monitoring performance of an aircraft windshield includes a sensor comprising a sensory contact and an evaluation unit. The sensory contact is in physical contact with one or more components of the windshield, and generates a signal representative of the performance of the component(s) of the windshield. An electrical connector is secured to the surface of the windshield facing the interior of the aircraft. The signal from the sensory contact passes through the connector to the evaluation unit. The evaluation unit acts on the signal to determine the performance of the component(s) of the windshield, wherein the evaluation unit is spaced from and out of physical contact with the windshield and the electrical connector, and is in electrical contact with the electrical connector.

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 window assembly heat transfer system is disclosed in which a window member has a selected transparency to monitored or sensed electromagnetic wavelengths. One or more passages are provided in the window member for flowing a single-phase or two-phase heat transfer fluid. 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.