A delivery container assembly for receiving a package. The delivery container assembly includes a container having at least one wall and an open top end defining a storage space. The container includes a lid hingedly coupled to the container and is movable between an open position and a closed position. The container includes an elevator assembly disposed within the container and including an elevator floor movable between a lowered position and a raised position. The lid is movable from the closed position to the open position upon movement of the elevator floor from the lowered position to the raised position.

A data storage system that moves and transfers components (e.g., the data storage cartridges, data storage magazines, etc.) utilizing drone systems is disclosed. In one embodiment, the system comprises at least one data storage library for storing, reading, and writing of data to or on a plurality of data storage cartridges and at least one drone vehicle. The system also includes a processing device and a non-transitory, computer-readable memory containing programming instructions. The programming instructions are configured to cause the processing device to receive a request to transfer a data storage component to a destination location, in response to receiving the request, instruct a drone vehicle to perform at least part of the transfer of the data storage component to the destination location, and by the drone vehicle, perform at least part of the transfer of the data storage component to the destination location. In accordance with another embodiment, a drone vehicle for transferring data storage components is disclosed. According to yet another embodiment, a method of transferring data storage components within a data storage system utilizing drones is disclosed.

A cycloidal rotor is provided having a flexible by actuators or self-flexing blade-positioning tack, which can be brought into shape corresponding to currently desired blade orbit. This rotor can also be provided with frontal shielding or partial enclosure to assure that rotor operates at any speed as if in hovering flight; rotor track can be inclined to produce forward thrust or external thrusters can be used. Optionally in other embodiments blade orbit shape is determined by a variable cam mechanism or the inclination of blade positioning track of fixed shape to produce a change of its projected shape onto blades' plane of operation thus changing blades elliptic orbit. Blade centrifugal force countervailing mechanism is also proposed.

Provided is a flight efficiency improving system for a compound helicopter with a rotor and fixed wings. In forward flight of the compound helicopter, the flight efficiency improving system does not perform a cyclic pitch control of the rotor so as to allow a difference in lift generated by the rotor between an advancing side and a retreating side of the rotor, or the flight efficiency improving system performs the cyclic pitch control to an extent that does not completely eliminate the difference. The fixed wings are provided respectively on left and right sides of a body and are asymmetric to each other so that influence of an aerodynamic interference between the rotor and the fixed wings is reduced.

A multi-segment oblique flying wing aircraft which has three distinct segments including two outer wing segments and a central wing segment. The central segment may be thicker in the vertical direction and adapted to hold pilots and passengers. The outer wing segments may be substantially thinner and may taper as they progress outboard from the wing center. The multi-segment oblique flying wing aircraft be adapted for rotating into a high speed flight configuration, or may be adapted for take-off and cruise at a constant angle. In an extreme flight case, the central wing segment may rotate to a local sweep of ninety degrees.

Disclosed are embodiments of flow diverting lift elements which, when placed in the proper orientation and propelled through a fluid, produce a lift force with improved lift versus velocity performance. The flow diverting lift elements can produce lift for rotary lift devices such as aircraft. The flow diverting lift devices include an airfoil and a diversion wall extending from an upper surface of the airfoil. The airfoil can be an annular airfoil.

A low energy consumption high-speed flight method, a wing ring mechanism, a flying saucer with wing rings, and a high-altitude power generation ring and an oppositely-pulling hovering-flight machine with the wing ring mechanism using the same are provided. The method enables the wing rings to tilt axially. The wing ring mechanism has the wing rings, a wing-ring rotating assembly, and wing-ring deflecting members each including a telescopic member and movable connecting members. The high-altitude power generation ring has the wing ring mechanism and cables. The wing ring mechanism is connected to the upper end of the cable that is connected to a part of a side of the wing ring mechanism; and the lower end of the cable is connected to a ground tie point. The oppositely-pulling hovering-flight machine uses two or two sets of aerostats or aircrafts that are respectively located in two airflows with opposite wind directions.

A system for modular aircraft includes at least a common component, wherein the at least a common component includes at least a flight component. The system includes at least a modular component, wherein the at least modular component includes at least a fuselage component and a collar component. The system includes at least an interface component, wherein the at least an interface component is configured to connect the at least a common component at a first end to the at least a modular component at a second end.

A system for modular aircraft includes at least a common component, wherein the at least a common component includes at least a flight component. The system includes at least a modular component, wherein the at least modular component includes at least a fuselage component and a collar component. The system includes at least an interface component, wherein the at least an interface component is configured to connect the at least a common component at a first end to the at least a modular component at a second end.

An unmanned vehicle having a launch configuration and one or more operational configurations. In the launch configuration, one or more engines resides within an engine bay. The unmanned vehicle is generally shaped like a projectile and can be launch from any tube-shaped deployment system using an initial propulsor. The engine bay can be opened, and the engines can be moved into a generally external position with respect to the engine bay for operation of said engines. In some embodiments, the one or more engines can pivot to direct thrust in multiple directions. In some embodiments, the unmanned vehicle includes flight control surfaces to further improve the flight characteristics of the vehicle.