Abstract: An aircraft window configuration utilizes a laminate build-up of the primary pane to increase damping and reduce the structural response to the turbulent boundary layer outside the aircraft. The laminate may consist of several acrylic layers or a combination of acrylic and glass layers. Noise dampening results from the introduction of a transparent visco-elastic material or a urethane. A vacuum layer may be introduced between the primary pane and a middle, or fail-safe pane. The vacuum layer decouples the panes over a broad frequency range resulting in a lower response of the inner pane that radiates noise into the passenger cabin. Such a window configuration reduces weight and improves noise performance. A damped laminate also reduces pane deflections into the air stream and improves aerodynamic performance of the aircraft.

Abstract: A window assembly and method for use with a mobile platform, and particularly with commercial or military aircraft. The window assembly includes a composite window panel that is secured to the fuselage skin of the aircraft. A tempered glass fairing is used in connection with a retainer clip and a plurality of sealing components to seal the fairing over the window panel in a manner that provides a sealed air gap between the inner surface of the fairing and the outer surface of the window panel. The fairing and the sealed air gap help to thermally isolate the window panel from the significant ambient temperature changes that are encountered during flight of the mobile platform. The fairing also provides a hazard barrier to protect the composite window panel from impact by foreign objects during flight. The sealed air gap also helps to control deflection of the fairing to thus ensure that the fairing maintains an aerodynamic profile generally in accordance with the contour of the outer surface of the fuselage.

Abstract: A system and a method is provided for fitting an aircraft cabin with modular sidewall panels, window reveals, and foam insulation blocks in an integrated manner. The system comprises a sidewall panel which may have one or more openings therethrough to receive a window reveal held by snap-fit fastenings. The bezel of the window reveal may be held by snap-fit fasteners for easy removal to allow removal and cleaning of the inner dust cover disassembly of the sidewall panel. Foam insulation blocks may be molded to fit in the cavity between the outer wall of the aircraft and the sidewall panels, held in place by compressive pressure between the frames of the airframe. The outer extent of the window reveal is tapered inwardly to guide the window reveal to mating contact with an outer window assembly in the aircraft fuselage without further adjustment of the sidewall panel.