Abstract: A translucent composite material comprises a substrate and a plurality of glass fibers embedded within the substrate. The substrate may comprise a substantially continuous nonwoven, non-fabric, translucent thermoplastic polyphenylsulfone substrate. The plurality of glass fibers may substantially span across a length of the substrate and may have an orientation, a fiber thickness, and a fiber area density selected to provide the translucent composite material with a strength, a flame-resistance, and a light transmissivity.

Abstract: A layered material for use in transparent, flame resistant components couples a thin, fire resistant outer polymeric film to a thicker, transparent inner polymeric material. The resultant transparent layered material meets FAA flammability requirements for OSU heat release, has excellent solvent resistance and cleanability, is scratch resistant, and is transparent enough for use in interior applications in the aerospace industry. The layered material is formed via a co-extrusion or co-lamination process.

Abstract: A translucent composite material that can be used in various airplane interior applications that allows sufficient light transmissivity while preferably meeting Federal Aviation Administration (FAA) flammability requirements for overhead materials in the cabin of a commercial aircraft. The material also meets FAA standards regarding vertical burn, smoke emissions tests, and toxic fume emissions tests. The composite material is formed by laminating long glass fibers and (PPSU) into a composite sheet under controlled heat and pressure. The composite sheet is then cut, bent or thermoformed to form the desired part. The parts formed are available for a wide variety of uses within the passenger cabin of a commercial aircraft. The long glass fibers may be unidirectional or weaved into a glass cloth like material. While preferably formed for airplane interior applications, these components may also be used in other aerospace or non-aerospace applications.

Abstract: An apparatus and method for making a mold or mold face includes a container having at least one opening. The apparatus also includes a flexible membrane that is retained to the container that extends across the opening of the container. The apparatus for making a mold further includes support media that is disposed within the container along with a vacuum valve that is connected to the container.

Abstract: A translucent composite material that can be used in various airplane interior applications that allows sufficient light transmissivity while preferably meeting Federal Aviation Administration (FAA) flammability requirements for overhead materials in the cabin of a commercial aircraft. The material also meets FAA standards regarding vertical burn, smoke emissions tests, and toxic fume emissions tests. The composite material is formed by laminating long glass fibers and (PPSU) into a composite sheet under controlled heat and pressure. The composite sheet is then cut, bent or thermoformed to form the desired part. The parts formed are available for a wide variety of uses within the passenger cabin of a commercial aircraft. The long glass fibers may be unidirectional or weaved into a glass cloth like material. While preferably formed for airplane interior applications, these components may also be used in other aerospace or non-aerospace applications.

Abstract: An apparatus and method for making a mold or mold face includes a container having at least one opening. The apparatus also includes a flexible membrane that is retained to the container that extends across the opening of the container. The apparatus for making a mold further includes support media that is disposed within the container along with a vacuum valve that is connected to the container.

Abstract: There is provided an ultrasonic welding apparatus that includes a magnetic source and a ferromagnetic device to apply pressure to at least one component being joined during the ultrasonic welding process. The magnetic source is positioned proximate the ultrasonic transducer, and when the component to be ultrasonically welded is adjacent the ultrasonic transducer, the ferromagnetic device is positioned opposite the component from the magnetic source and the ultrasonic transducer to apply pressure. A magnetic source comprising an electromagnet provides an adjustable pressure to the component. The ferromagnetic device defines a generally spherical surface so that it advantageously remains in position relative to the magnetic source if the component is moved relative to the ferromagnetic device. In addition, the ferromagnetic device may comprise a magnet to increase the magnetic force between the magnetic source and ferromagnetic device, which increases the pressure applied to the component.

Abstract: A semi-rigid, light weight insulation blanket is composed of a skeleton having porous cavities sandwiched between layers of fiber glass. The polyimide foam skeleton prevents sagging particularly in crown and upper sidewall areas of an aircraft thereby maintaining a predetermined offset from the skin fuselage reducing corrosion of the primary structure from moisture condensate. This configuration provides similar acoustic performance with reduced weight.

Abstract: A semi-rigid, light weight insulation blanket is composed of a skeleton having porous cavities sandwiched between layers of fiber glass. The polyimide foam skeleton prevents sagging particularly in crown and upper sidewall areas of an aircraft thereby maintaining a predetermined offset from the skin fuselage reducing corrosion of the primary structure from moisture condensate. This configuration provides similar acoustic performance with reduced weight.