Abstract: A joule-heating press and method for manufacturing a metallic honeycomb core via diffusion bonding. The method may include printing a pattern of strips of a stop-off material to surfaces of a plurality of sheets of metal at locations where diffusion bonding is not desired and stacking the sheets of metal together in a sequence for forming the honeycomb core. Then the method may include steps of pressing the sheets of metal together between two press plates made of conductive material and applying electric current to the conductive material of the press plates. This allows current to flow through a thickness of the sheets of metal and the sheets of metal are thereby diffusion bonded to each other via joule heating at locations absent the stop-off material. Finally, the method may include a step of expanding the sheets of metal into the honeycomb core.

Abstract: An aircraft nacelle comprising an outer cowl having an inner wall and an outer wall surrounding the inner wall. The inner wall may have an inner opening formed therethrough and the outer wall may have an outer opening formed therethrough at an aft end of the nacelle. The nacelle may further comprise a translating panel configured to cover the inner and outer openings in a stowed position and to translate aft to a deployed position. The translating panel may be fixed to cascade guide vane panels which rest between the inner and outer wall in the stowed position and are exposed to airflow via the inner and outer openings when translated aft to the deployed position, thereby increasing a nozzle area of the nacelle. Guide vanes of the cascade guide vane panels are angled slightly aftward to direct the nacelle's airflow outward and aftward.

Abstract: A method and apparatus for fabricating a composite part, such as a fuselage or internal stiffener, with a shape memory polymer (SMP) apparatus usable as a rigid lay-up tool. The SMP apparatus may be heated until malleable, shaped, and then cooled in a desired rigid tool configuration. For example, cavities may be formed into the SMP apparatus for nesting components therein to co-bond or co-cure with the composite part. The composite material and/or nested components may be heated and compressed against the SMP apparatus. The SMP apparatus may be configured to remain rigid during the composite cure cycle. Once the composite material is cured, the SMP apparatus may be triggered to a malleable state and urged away from the cured composite material.