An in-flight battery recharging system for Unmanned Aerial Vehicle (UAV). This invention converts byproducts of a multi-rotor unmanned aerial vehicle's conventional propulsion system operation and airframe movements to generate electricity that, in turn, is used to power the propulsion system's electric motors, power onboard electronic components, and recharge the battery that initially powers the propulsion system's electric motors. Having this ability of recharging the battery in-flight gives an unmanned aerial vehicle a much improved flight time and range, thereby greatly increasing its utility.

An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A plurality of hydraulic or electric motors are disposed within or attached to the closed wing, fuselage or spokes in a distributed configuration. A propeller is proximate to a leading edge of the closed wing or spokes and operably connected to each hydraulic or electric motor. A source of hydraulic or electric power is disposed within or attached to the closed wing, fuselage or spokes and coupled to each hydraulic or electric motor disposed within or attached to the closed wing, fuselage or spokes. A controller is coupled to each hydraulic or electric motor, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.

An aircraft capable of vertical takeoff and landing and stationary flight includes a distributed airframe coupled to a modular fuselage. The modular fuselage has a longitudinal axis substantially parallel to a rotational axis of three or more propellers. The modular fuselage includes a rear module substantially disposed within a perimeter of the distributed airframe, a front module removably connected to the rear module and substantially aligned with the longitudinal axis. One or more engines or motors are disposed within or attached to the distributed airframe or fuselage. The three or more propellers are proximate to a leading edge of the distributed airframe, distributed along the distributed airframe, and operably connected to the one or more engines or motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight.

A hybrid aerial vehicle (HAV) comprising: a fuselage of the HAV; a first mechanism within the fuselage for accepting a plurality of wings of the HAV, the first mechanism allowing coordinated contraction of the plurality of wings essentially into the fuselage such that tips of the wings are position in proximity of the fuselage and coordinated extension of the wings such that tips of each wing are positioned away from the fuselage; a first wing extending from the port side of the fuselage and connected to the first mechanism; a second wing extending from the starboard side of the fuselage and connected to the first mechanism; a second mechanism placed within the fuselage in proximity to its front end, the second mechanism allowing motion of propellers of the HAV affixed there to between a first plain and a second plain; a first set of propellers affixed at the port side of the fuselage to the second mechanism; a second set of propellers affixed at the starboard side of the fuselage to the second mechanism; a third mechanism placed within the fuselage in proximity to its rear end, the third mechanism allowing motion of propellers of the HAV affixed there to between a first plain and a second plain, and further placing the propellers affixed thereto to be at a vertical displacement with respect to the propellers affixed to the second mechanism; a third set of propellers affixed at the port side of the fuselage to the third mechanism; and a fourth set of propellers affixed at the starboard side of the fuselage to the third mechanism.

A flying wing vertical take-off and landing (VTOL) aircraft includes an empennageless-fuselage from which foldable wings extend outwardly, an empennageless-nacelle supported on each of the wings and a rigid rotor propeller disposed on each empennageless-nacelle, each of the propellers being drivable to rotate about only a single rotational axis defined along a longitudinal axis of the corresponding empennageless-nacelle and being fully cyclically controllable.

A method of using a bagged power generation system comprising windbags and waterbags integrated with drones and adapting drone technologies for harnessing wind and water power to produce electricity. An extremely scalable and environmentally friendly method, system, apparatus, equipment, techniques and ecosystem configured to produce renewable green energy with high productivity and efficiency.

A virtualized infrastructure for guiding delivery drones, a drone delivery method, and a wingless delivery drone are disclosed that includes a container for storing payloads; a plurality of thrust motors arranged in an array on an X-Y surface below and parallel to a bottom surface of the payload container; and a drone electrical system configured to control the operations of the array of the thrust motors so as to fly the container from the first address to the destination address upon receiving the optimal flight route from the virtualized infrastructure and to maintain the balance to payload container.

A dual mode turbofan engine includes a jet engine portion having a compressor, a turbine disposed aft of the compressor, and a shaft coupled to the compressor and the turbine. The jet engine portion is configured to produce an exhaust. The system further includes an auxiliary turbine having a plurality of auxiliary turbine blades. The auxiliary turbine is disposed aft of the turbine and decoupled from the shaft. The system also includes a diverter disposed between the turbine and the auxiliary turbine. The diverter is configured to selectively direct the exhaust to an inner flow path bypassing the plurality of auxiliary turbine blades or to an outer flow path engaging the plurality of turbine blades. A plurality of propeller blades is hingedly connected to the auxiliary turbine.

Balancing a drone is difficult with engines, when drones are equipped with engines to increase the flight time. However, balancing the drone can be made easy by providing the drone with an electric motor or an electric motor that involves a generator feature.

Disclosed herein is a flying taxi for facilitating the transportation of payloads, in accordance with some embodiments. Accordingly, the flying taxi may include a pod, a processing device, a presentation device, and an aerial vehicle. Further, the pod may be configured to receive a payload. Further, the pod may include a weight sensor disposed on the pod. Further, the weight sensor may be configured to generate a weight data corresponding to a weight of the payload. Further, the processing device may be communicatively coupled with the weight sensor. Further, the processing device may be configured for analyzing the weight data. Further, the processing device may be configured for generating a notification based on the analyzing. Further, the presentation device may be communicatively coupled with the processing device. Further, the aerial vehicle may be detachably couplable with the pod using a coupling mechanism.