A hub assembly for a rotary wing aircraft having a rotor shaft which rotates about a rotational axis includes: a hub extender arm coupled to the rotor shaft; a pitch bearing that is disposed within and connected to the hub extender arm; and a rotor blade assembly having an inboard section disposed within the hub extender arm and connected to the pitch bearing; wherein the hub extender arm has an inboard cross-sectional area where coupled to the rotor shaft that is greater than an outboard cross-sectional area where coupled to the pitch bearing.

An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.

An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight. An aerial vehicle able to quickly alter its thrust. A quick reaction propeller system which alters the pitch of the propeller blades in response to changes in coning angle of the propeller.

An aerial vehicle adapted for vertical takeoff and landing using pivoting thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to takeoff with thrust units providing vertical thrust and then transitioning to a horizontal flight path. An aerial vehicle with pivoting thrust units with propellers, wherein some or all of the propellers are able to be stowed and fully nested during forward flight. An aerial vehicle able to quickly alter its thrust. A quick reaction propeller system which alters the pitch of the propeller blades in response to changes in coning angle of the propeller.

The present invention relates to Tetracyclic Heterocycle Compounds of Formula

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and pharmaceutically acceptable salts or prodrug thereof, wherein A, X, R.sup.1, R.sup.2, R.sup.3 and Ware as defined herein. The present invention also relates to compositions comprising at least one Tetracyclic Heterocycle Compound, and methods of using the Tetracyclic Heterocycle Compounds for treating or preventing HIV infection in a subject.

An apparatus is provided for rotational equipment. This apparatus includes a rotor blade including an airfoil body, a spar structure and a cuff. The airfoil body extends spanwise from a base to a tip. The airfoil body extends longitudinally (e.g., chordwise) from a leading edge to a trailing edge. The airfoil body extends laterally between a first side and a second side. The spar structure extends spanwise within and supports the airfoil body. The cuff projects out from the spar structure and away from the base of the airfoil body. The cuff is formed integral with the spar structure. The cuff and the spar structure are configured from or otherwise include thermoplastic material.

A rotorcraft includes a rotor hub coupled to a mast and a plurality of rotor extensions. Each rotor extension is configured to secure a rotor blade to the rotor hub and includes a first connector configured to attach the rotor extension to a rotor blade, a second connector configured to attach the rotor extension to the rotor hub; a shaft disposed between the first and second connectors, and a damper mount attached to the second connector. The rotorcraft also includes a fairing enclosing the damper and at least a portion of the rotor hub.

Embodiments of the present application relate to the field of propeller technology and specifically disclose a propeller, a propeller kit, a power assembly, a power kit and an unmanned aerial vehicle (UAV). The propeller includes a hub and at least two blades connected to the hub. The hub is detachably mounted on a corresponding drive apparatus by a mounting member corresponding to the hub, so that the propeller is mounted on the corresponding drive apparatus. A surface, facing the mounting member, of the hub is provided with a first fitting portion. A surface, facing the hub, of the mounting member is provided with a second fitting portion corresponding to the first fitting portion. The first fitting portion matches the second fitting portion. In the foregoing manner, a user can be prevented from incorrectly mounting a forward propeller and a counter-rotating propeller during the use of a quick-detachable propeller in the embodiments of the present application.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes.