The present invention relates to Tetracyclic Heterocycle Compounds of Formula ##STR00001##
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 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.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements 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. The aerial vehicle uses deployment mechanisms to deploy rotor assemblies up and away from their stowed configuration locations.

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements 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. The aerial vehicle uses deployment mechanisms to deploy rotor assemblies up and away from their stowed configuration locations.

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.

A ducted fan for an aircraft includes a rotor-side fan and a stator-side duct that surrounds the rotor-side fan. The stator-side duct includes an inner wall facing the rotor-side fan and an outer wall averted from the fan. The ducted fan further includes a fastening device configured to support mounting of the ducted fan on a structural component of the aircraft. The fastening device includes a pin and a guide body. The guide body is configured to receive and guide the pin, the pin is insertable proceeding from the inner wall into a recess of the guide body, a first end of the pin protrudes relative to the outer wall, and the pin is configured to be mounted, via the first end, on a bearing of the structural component of the aircraft.

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.

A rotor assembly configured to increase the stiffness of a rotor mast. The rotor assembly includes the rotor mast, a rotor hub, a mast nut, a mast bearing, and a cuff disposed between the mast nut and the mast bearing. The cuff is captured and compressed between the mast nut and the inner race of the mast bearing along an uninterrupted load path that extends between the mast nut and the mast bearing.

A rotor assembly configured to increase the stiffness of a rotor mast. The rotor assembly includes the rotor mast, a rotor hub, a mast nut, a mast bearing, and a cuff disposed between the mast nut and the mast bearing. The cuff is captured and compressed between the mast nut and the inner race of the mast bearing along an uninterrupted load path that extends between the mast nut and the mast bearing.