Abstract: A method of producing a reinforced duct structure for use with turbo-fan aircraft engines and the like. The duct is first cut from a flat metal sheet in a predetermined pattern. The sheet is rolled to form a tubular or conic structure of the approximate desired configuration and welded along the open seam. The welded tubular structure is then expanded to the exact required shape. The expanded tubular structure is cut out in selected areas to form a tubular grid structure. A tubular liner conforming to the inner surface of the tubular grid structure is installed and bonded to the grid structure forming an integral tubular structure of the desired configuration and strength and; attachment of any required mating flanges and structure bosses to the integral tubular structure.

Abstract: Method of fabricating attenuation sandwich panels having a central cellular core positioned between and bonded to an imperforate facing sheet on one surface thereof and a perforate facing sheet with an outer layer of porous fibrous material adhered to the other surface. The combined perforate sheet and porous fibrous material have a predetermined open surface area prior to attenuation panel fabrication. The porous fibrous surface is then saturated with a combined liquidous anti-wetting and indicator solution which coats substantially all of the fibers. The solution is allowed to dry and the opposite side is inspected for any indicator present. If indicator is detected on the opposite side of the perforate sheet from the porous fibrous material, it is removed therefrom. The components making up the panel are then assembled and bonded together to form the attenuation panel.

Abstract: A relatively simple variable area divergent exhaust nozzle and low drag afterbody integrated with a target-type thrust reverser and used in conjunction with a convergent nozzle for application to the propulsion system of a high performance jet powered aircraft. Two or more aerodynamically shaped afterbody surfaces may be pivoted with a common actuation system to form: first an efficient nozzle-afterbody suitable for subsonic operation; second, a divergent nozzle-afterbody for efficient supersonic operation and; third, a target-type thrust reverser for in-flight or ground roll deceleration.

Abstract: A streamline shroud surrounding a jet aircraft engine terminates forwardly of the aft end of the engine tail pipe, which comprises a secondary nozzle. Two or more deflector doors in stowed position combine to form a sleeve surrounding the aft portion of the tail pipe, and the trailing edges of these doors extend downstream and converge beyond the tail pipe to form a primary nozzle, which has an exit flow area smaller than that of the secondary nozzle, and of proper size and configuration to provide required mass flow, velocity and pressure for normal flight operation. The doors swing outwardly and rearwardly on linkage carried by the sponsons to a deployed position spaced aft of the tail pipe and disposed transversely to the tail pipe axis to deflect flow laterally and nullify thrust.