Abstract: An apparatus to protect exposed structures on an aircraft which includes a core; a securing mechanism coupled to the core; and an outer coating applied to the core to encapsulate the core and facilitate the attachment of the securing mechanism. A thermal protection layer may be applied to the apparatus for high temperature applications.

Abstract: A exposed edge protection device molded from an elastomer or a combination of elastomers of varying durometers formed together to match the outer mold line of an exposed edge. The device may include encapsulated flexible magnets providing for a durable monolithic device produced cost-effectively in a single-step process.

Abstract: An apparatus to protect exposed structures on an aircraft which includes a core; a securing mechanism coupled to the core; and an outer coating applied to the core to encapsulate the core and facilitate the attachment of the securing mechanism. A thermal protection layer may be applied to the apparatus for high temperature applications.

Abstract: A method for repairing a high temperature composite structure fabricated from layers of composite plies. If the composite structure contains an internal high temperature core, the core is first restored by installing a core block into the damaged region, bonding the core block in place by applying high temperature material resin and uncured foam material into the region between the core block and the damaged region, and partially curing the core block. A number of repair plies, formed from pre-impregnated composite material or formed using dry cloth manually impregnated with high temperature resin are prepared. The repair plies are sized and shaped using a series of templates corresponding to the damaged region. The installed plies are cured using high temperature localized heating of the damaged region without impairing the surrounding structure.