Abstract: A method of fabricating a vacuum barrier system includes fabricating a soluble forming mandrel, laying up composite material over the soluble forming mandrel, and applying a forming mandrel vacuum bag over the composite material and curing the composite tooling material to form a cured composite bag carrier. The method also includes de-bagging and trimming the cured composite bag carrier.

Abstract: A vacuum barrier system for curing a composite part may include a bag carrier and a compliant, relatively thin film bladder formed over the bag carrier to function as a vacuum barrier. The bag carrier may be configured complementary to the composite part. The bladder may seal the bag carrier therewithin.

Abstract: A method of fabricating a vacuum barrier system includes fabricating a soluble forming mandrel, laying up composite material over the soluble forming mandrel, and applying a forming mandrel vacuum bag over the composite material and curing the composite tooling material to form a cured composite bag carrier. The method also includes de-bagging and trimming the cured composite bag carrier.

Abstract: A system and method for operating an ice detection and deicing system are provided herein. The ice detection and deicing system may use changing magnetic properties of various components caused by temperature changes to detect conditions conducive to, or indicating, ice formation. The ice detection and deicing system may further use eddy currents induced in one or more layers of the system to increase the temperature of the one or more layers to reduce the amount of ice formation or reduce the probability of ice being formed.

Abstract: A method comprises laying up a fiber ply of reinforcing fibers and a metal foil layer in a full face-to-face relation. The fibers in the fiber ply are oriented in a single direction. The metal foil layer includes a plurality of metal foil strips separated by gaps. The metal foil layer has substantially the same length and width as the fiber ply. The method further comprises infusing resin into the layup, wherein the resin flows through the gaps and infuses into the fibers.

Abstract: Systems and methods provide for edge protection and visual damage indication for a composite blade stringer. According to one aspect, an edge protection and visual indication system may be an edge treatment provided over an outer edge of a web of a composite blade stringer. The edge treatment may include a number of material layers encompassing the outer edge of the web and extending from a first surface of the web to a second surface of the web. The material layers may include a color contrasting layer and fiberglass layers. The material layers may alternatively include two overlapping, pre-cured angles.

Abstract: A system and method for operating an ice detection and deicing system are provided herein. The ice detection and deicing system may use changing magnetic properties of various components caused by temperature changes to detect conditions conducive to, or indicating, ice formation. The ice detection and deicing system may further use eddy currents induced in one or more layers of the system to increase the temperature of the one or more layers to reduce the amount of ice formation or reduce the probability of ice being formed.

Abstract: A method comprises laying up a fiber ply of reinforcing fibers and a metal foil layer in a full face-to-face relation. The fibers in the fiber ply are oriented in a single direction. The metal foil layer includes a plurality of metal foil strips separated by gaps. The metal foil layer has substantially the same length and width as the fiber ply. The method further comprises infusing resin into the layup, wherein the resin flows through the gaps and infuses into the fibers.

Abstract: A method for fabricating a laminated composite body including a metal foil and a plurality of fiber plies. The method includes perforating a sheet of metal foil, stacking the perforated metal foil sheet and the plurality of fiber plies in face to face relation in a predetermined order and orientation, and infusing resin into the stacked sheet and plies so that resin flows through the perforations in the metal foil sheet and intersperses between the plurality of fiber plies to form the laminated composite body.

Abstract: A single pane window for use in a jet aircraft. The single pane window includes a plurality of metal sheets. A fiber reinforced resin at least partially surrounds the plurality of metal sheets. The fiber reinforced resin is transparent. A cutout is formed within each of the plurality of metal sheets, with the cutout being filled by the transparent resin during the manufacturing process. The cutout forms an optically transparent window portion of the single pane window. The single pane window is lightweight and strong enough to form a load bearing portion of a fuselage of a commercial aircraft into which it is incorporated, and also does not require the bulky and heavy frame structure that has traditionally been required on window structures of jet aircraft. The single pane window also enables even larger windows to be incorporated on aircraft without increasing the weight or cost associated with such windows.

Abstract: An aircraft that has a structural skin panel. The structural skin panel has: at least one metal sheet having a cutout portion and a perimeter portion, the perimeter portion having a plurality of spaced apart perforations formed therein; and first and second fiber reinforced performs that are generally transparent and that sandwich the at least one metal sheet therebetween and overlay the perimeter portion. An optically transparent resin saturates the first and second fiber reinforced performs and fills the perforations in the at least one metal sheet. Portions of the fiber reinforced preforms that overlay the cutout form a window portion in the structural skin panel.

Abstract: A transparent skin panel for use in a mobile platform having a plurality of metal sheets. A fiber reinforced resin at least partially surrounds the plurality of metal sheets. The fiber reinforced resin is transparent. A cutout is formed within each of the plurality of metal sheets, which is filled by the transparent resin during the manufacturing process. The cutout corresponds to a window in the transparent skin panel. The transparent skin panel thus eliminates the need for a bulky and heavy frame structure that has traditionally been employed on aircraft, and which has heretofore limited the size of windows used on an aircraft. The present invention thus enables larger windows to be incorporated on aircraft without increasing the weight or cost associated with such windows.

Abstract: A transparent skin panel for use in a mobile platform having a plurality of metal sheets. A fiber reinforced resin at least partially surrounds the plurality of metal sheets. The fiber reinforced resin is transparent. A cutout is formed within each of the plurality of metal sheets, which is filled by the transparent resin during the manufacturing process. The cutout corresponds to a window in the transparent skin panel. The transparent skin panel thus eliminates the need for a bulky and heavy frame structure that has traditionally been employed on aircraft, and which has heretofore limited the size of windows used on an aircraft. The present invention thus enables larger windows to be incorporated on aircraft without increasing the weight or cost associated with such windows.