Abstract: Load management system and methods are described for aircraft, including tailsitters. A load management system can comprise a pole coupled the fuselage and free to rotate and swing. The pole can comprise a cargo hook and a distal end that can be releasably coupled to a cargo cable or cargo. The pole can be coupled near its distal end to a retractable cable that is deployed from a position aft of the pole. During landing, takeoff, and when otherwise in hover mode, the retractable cable can be retracted—holding the pole along or near the fuselage. During transition to, or during, flight mode, the retractable cable can be deployed which can harmonize the cargo's center of gravity with the needs of the tailsitter aircraft.

Abstract: There is disclosed in one example a mechanical assembly, including: a parent part including a parent part lug; a bushing to pass through the lug, the bushing comprising a central inner diameter, and respective left and right relief zones having a second inner diameter different from the central inner diameter; and a through-pin to pass through the bushing.

Abstract: In one embodiment, a rotor hub comprises a hub plate, a yoke for attaching a plurality of rotor blades, a plurality of yoke support bearings, and a plurality of cushioned damper bearings for attaching a plurality of dampers.

Abstract: According to one embodiment, a gear includes a steel portion that is oriented on a center axis. The steel portion includes a hub, a cylindrical rim, a web, and a plurality of engagement features. The hub is centered about the center axis. The rim has an exterior surface and an interior surface that surrounds the hub and is centered about the center axis. The web extends from an exterior surface of the hub to the interior surface of the rim. The engagement features are on the exterior surface of the cylindrical rim. The gear also includes a first composite piece adjacent to a first side of the web, the first composite piece extending from the hub to the interior surface of the rim, wherein the first composite piece does not extend past the hub towards the center axis.

Abstract: In one embodiment, a rotor hub comprises a hub plate, a yoke for attaching a plurality of rotor blades, a plurality of yoke support bearings, and a plurality of cushioned damper bearings for attaching a plurality of dampers.