Abstract: A method of producing an article of manufacture includes printing a break-wire conductive-material pattern via an additive-manufacturing process and applying the break-wire conductive-material pattern to a surface of a component. A shape of the break-wire conductive-material pattern fits the surface of the component.

Abstract: Systems and techniques for controlling a power distribution of a hybrid powertrain system using magnetorheological (MR) clutches. In embodiments, MR clutches may be used to control the power transfer from a mechanical power source to a plurality of loads. For example, mechanical power produced by a mechanical power source (e.g., an internal combustion engine (ICE)) may be transferred to each load of the plurality of loads using an MR clutch respectively connected to each load. In this example, the amount of mechanical power transferred from the mechanical power source to each of the loads of the plurality of loads may be controlled and/or managed using the MR clutch connected to each respective load. In embodiments, a load may be engaged or disengaged from the mechanical power source gradually, such as by ramping up or ramping down the amount of mechanical power transferred via the MR clutch to the load.

Abstract: An apparatus for introducing a test load to a rotor blade test specimen for fatigue testing includes a body extending along a longitudinal axis in a first direction from a first end to a second end, and the body having an internal cavity with an opening at the second end configured to dispose a tip portion of the rotor blade test specimen.

Abstract: An aircraft includes a fuselage, and a wing extending from the fuselage along a spanwise axis. A section of the wing is rotatable about the spanwise axis. A ducted fan is mounted to the section of the wing. The ducted fan has a hub configured to be drivingly engaged by an engine. The hub is rotatable about a fan axis. Blades protrude from the hub between roots mounted to the hub and tips radially spaced from the hub. A duct circumferentially extends about the fan axis and is mounted to the tips of the blades to rotate with the blades about the fan axis. The section of the wing and the ducted fan are rotatable about the spanwise axis between a hover mode in which the fan axis is substantially perpendicular to a ground, and an aircraft mode in which the fan axis is substantially parallel to the ground.

Abstract: Systems and methods for testing and validating fatigue life of a complex structure includes determining flight loads acting on the complex structure, identifying fatigue sensitive points in the complex structure in response to the flight loads acting on the complex structure, grouping the fatigue sensitive points into a plurality of families, selecting at least one representative fatigue sensitive point from each family, creating at least one detail specimen that replicates the representative fatigue sensitive point from each family, fatigue testing the detail specimens, and comparing results determined in response to fatigue testing the detail specimens to the determined flight loads.