Abstract: An encapsulated insulation composite system for increasing the burn through resistance of an aircraft fuselage includes: an insulation layer of glass fiber or foam insulation and a coating or interleaf barrier layer of a high temperature resistant material and/or a coating or barrier layer of a high temperature resistant material on an outer major surface of the insulation layer of the composite and a film encapsulating the composite. Preferably, the barrier layer or layers include a reflective mineral, such as a reflective mineral containing coating carried on a sheet material. Preferably, the encapsulating film is a polymeric film such as a polyimide film.

Abstract: An encapsulated insulation composite system for increasing the burn through resistance of an aircraft fuselage includes: an insulation layer of glass fiber or foam insulation and a coating or interleaf barrier layer of a high temperature resistant material and/or a coating or barrier layer of a high temperature resistant material on an outer major surface of the insulation layer of the composite and a film encapsulating the composite. Preferably, the barrier layer or layers include a reflective mineral, such as a reflective mineral containing coating carried on a sheet material. Preferably, the encapsulating film is a polymeric film such as a polyimide film.

Abstract: An encapsulated insulation composite system for increasing the burn through resistance of an aircraft fuselage includes: an insulation layer of glass fiber or foam insulation and a coating or interleaf barrier layer of a high temperature resistant material and/or a coating or barrier layer of a high temperature resistant material on an outer major surface of the insulation layer of the composite and a film encapsulating the composite. Preferably, the barrier layer or layers include a reflective mineral, such as a reflective mineral containing coating carried on a sheet material. Preferably, the encapsulating film is a polymeric film such as a polyimide film.

Abstract: An insulation product especially suited for use as an aircraft insulation includes a blanket of randomly oriented entangled glass fibers bonded together by a thermosetting binder and having a mean diameter of about 1+/−0.25 microns. The blanket has a density between about 0.25 and about 1.5 pounds per cubic foot and a thickness between about 0.35 inches and about 2.0 inches. The blanket, exclusive of anything else, has an average machine direction tensile strength of at least 0.6 pounds/inch of blanket width and an average cross machine direction tensile strength of at least 0.3 pounds/inch of blanket length; a transverse airflow resistance between about 300 Rayls and about 1800 Rayls; and a thermal conductivity equal to or less than about 0.32 BTU-in/hr-ft2-° F. The glass fibers of the blanket have a biodissolution rate in excess of 150 ng/cm2/hr.

Abstract: A cellular material, preferably a low density foam material, having an initial average normal incidence sound absorption coefficient for a selected frequency range is perforated to form a perforated cellular sound absorption material. The perforated cellular sound absorption material formed has an average normal incidence sound absorption coefficient for the selected frequency range greater than the initial average normal incidence sound absorption coefficient of the cellular sound absorption material. The depth(s), diameter(s), shape(s) and pattern of the perforations provide the cellular sound absorption material with the improved sound absorption properties that are reflected in the increased average normal incidence sound absorption coefficient of the material.