An article that includes a structured substrate having a macro-porous structure that defines a plurality of pores, and a metallic nano-crystalline coating on at least a portion of the structured substrate, where the metallic nano-crystalline coating defines an average grain size less than about 20 nanometers.

A system for on-wing engine washing and water reclamation is provided. The system has at least one spray device for introducing a cleaning liquid containing at least water into the engine while the engine is being operated, and an effluent trough for collecting the cleaning liquid from an exit end or underneath side of the engine. In a preferred embodiment, a source of the cleaning liquid and the effluent trough are located on a mobile unit. Further, a treatment system for treating the collected cleaning liquid is also located on a mobile unit.

A system for following the handling of an aircraft engine includes a cradle which supports the engine and stands which are spread out under the cradle. Each stand includes a seating configured to secure the stand on the ground, an actuating cylinder secured to the seating and having a translationally mobile piston, a fixing structure secured to the exterior end of the piston and configured to be fixed to the cradle, and a fluid source which causes the piston to be raised or lowered. Each stand also includes a detector designed to detect an inappropriate movement of the piston and a blocking which blocks the piston from moving when the detector detects an inappropriate movement of the piston. Thus, when an inappropriate movement of the piston is detected, the blocking blocks the movement of the cradle and prevents it from tipping.

A system for calculating forces exerted into an aircraft component includes a test hinge assembly and a monitoring system. In at least one embodiment, the test hinge assembly is a triangular shaped assembly, and includes at least one beam, at least one connecting joint having a channel configured to receive and retain a fastening member, and at least one strain gage secured to an outer surface of the beam(s). The strain gage(s) is configured to detect one or more strains exerted into the beam(s). The monitoring system is in communication with the strain gage(s). The monitoring system is configured to calculate forces exerted into the fastening member(s) by analyzing the strain(s) exerted into the beam(s).

A method and apparatus for holding a panel. A rigid frame is secured on an aircraft on a rework area on the aircraft. A carrier is attached to the rigid frame. The panel is held on the carrier and the carrier moves the panel about a plurality of axes. The panel moves with the carrier such that the panel has a desired position relative to a rework opening in the rework area. The panel is attached to the aircraft while the panel is held in the desired position relative to the rework opening.

A method and apparatus for performing manufacturing functions on a workpiece. The apparatus may comprise a base, a plurality of autonomous functional components, and a plurality of autonomous movement systems. Each functional component of the plurality of autonomous functional components may be configured to perform a respective function. The plurality of autonomous movement systems may be associated with the base. Each of the plurality of autonomous movement systems may be connected to a respective functional component of the plurality of autonomous functional components.

A method and apparatus for performing manufacturing functions on a workpiece. The apparatus may comprise a base, a plurality of autonomous functional components, and a plurality of autonomous movement systems. Each functional component of the plurality of autonomous functional components may be configured to perform a respective function. The plurality of autonomous movement systems may be associated with the base. Each of the plurality of autonomous movement systems may be connected to a respective functional component of the plurality of autonomous functional components.

A method and apparatus are presented. The apparatus comprises a first unitary structure, a second unitary structure, and a number of joints between the first unitary structure and the second unitary structure. The first unitary structure has a plurality of T-shaped cross-sections. The second unitary structure has a plurality of T-shaped cross-sections.

High-altitude balloons and apparatuses for filling such high-altitude balloons are provided. As an example, an apparatus for filling a high-altitude balloon includes a tube extending through envelope material of the balloon is provided. The apparatus also includes a flange connected to a first end of the tube. The flange is connected to an interior surface of the balloon. A fitting is connected to a second end of the tube. The fitting is configured for attachment with an apparatus for filling the balloon with lift gas. In addition, methods of filling high-altitude balloons with lift gas and methods of manufacturing balloons are also provided.

High-altitude balloons and apparatuses for filling such high-altitude balloons are provided. As an example, an apparatus for filling a high-altitude balloon includes a tube extending through envelope material of the balloon is provided. The apparatus also includes a flange connected to a first end of the tube. The flange is connected to an interior surface of the balloon. A fitting is connected to a second end of the tube. The fitting is configured for attachment with an apparatus for filling the balloon with lift gas. In addition, methods of filling high-altitude balloons with lift gas and methods of manufacturing balloons are also provided.