In order to reduce the weight of a hybrid propulsion system for a multi-rotor rotary-wing aircraft, the system comprises at least one inverter configured to supply power in parallel to multiple electric motors intended to drive the corresponding propellers of the system.

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 rotor wing aircraft provided with a propulsion apparatus is disclosed. The aircraft has a rotating mast configured to rotate said rotor wing and the apparatus includes a pole mechanically connectable to the rotating mast of the aircraft. At one of the ends of the pole there is placed an electric turbine, powered by a battery, and configured to rotate the pole around an axis of the rotating mast in such a way that the rotation of the pole can be used to rotate the rotor wing. Preferably the pole is made of carbon fiber.

The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, 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 energy-efficient launch system that utilizes the principles of whip dynamics to launch payloads at high speeds is described. The launch system may include a marine vehicle having an onboard power source. A tapered, superconducting cable may be retractably connected to the marine vehicle via a winch and electrically connected to the power source. One or more aerial vehicles may be coupled to and receive power via the cable. To launch a payload at the end of the cable, the marine vehicle, winch, and/or aerial vehicles may be operated in coordination to create, propagate, and accelerate a whip waveform along the cable toward the payload.

An aerial vehicle, such as an unmanned aerial vehicle, includes a fuselage having a forward end, an aft end, and a duct extending between said forward end and said aft end, said duct being oriented along a longitudinal axis of said fuselage; a primary propulsion unit mounted within said duct and generating lift for upward and downward motion while said fuselage is in a substantially vertical orientation and thrust for forward motion while said fuselage is in a substantially horizontal orientation; a plurality of airfoils each having a proximal end attached at opposite sides of the fuselage, said airfoils providing lift during forward motion of said fuselage; and a plurality of secondary propulsion units generating thrust to tilt the fuselage between said substantially vertical orientation and said substantially horizontal orientation.

A triaxial helicopter includes a fuselage and an airframe, and three rotor modules and a driving source are installed to the airframe, and two turbofans are mounted at the tail of the airframe, and the horizontal elevator is installed between the two turbofans and coupled to the driving source through a link rod module, so that when the triaxial helicopter is operated, the two turbofans are operated to produce a backward airflow to assist propelling the triaxial helicopter to move forward, so as to improve the flying speed of the triaxial helicopter. When it is necessary to ascend or descend the triaxial helicopter, the driving source controls the link rod module to adjust the yaw direction of the horizontal elevator according to an ascending or descending requirement, and the airflow produced by the turbofans blows in a direction with the horizontal elevator to increase the lifting force of the triaxial helicopter.

A turbocharged gas turbine engine with an electric generator to provide electrical power for an aircraft (e.g., UAV) with multiple propulsor fans each driven by an electric motor, where the engine includes a low spool that drives a main fan and a high spool that drives a high speed electric generator. The low pressure compressor supplies low pressure air to an inlet of the high pressure compressor. A row of stator vanes in the high pressure turbine is cooled using cooling air bled off from the low pressure compressor outlet that is passed through an intercooler and a boost compressor, where the spent vane cooling air is discharged into the combustor. The low pressure turbine and the two compressors each include a variable inlet guide vane to control the power level of the engine. Bypass flow from the main fan is used to cool hot parts of the engine.

A method of operating an aircraft according to an exemplary embodiment of this disclosure includes, among other possible things, communicating power from a storage device within an unmoved aerial vehicle (UAV) to an aircraft; controlling a propulsive device within the UAV with a control system of the aircraft to provide propulsive thrust to the aircraft; and detaching the UAV including the storage device and the propulsion device from the aircraft responsive to the energy within the storage device being below a predefined threshold.

In a hybrid flight vehicle, having multiple rotors attached to a frame, a gas turbine engine to drive the rotors; a generator connected to the gas engine to generate electric power, a battery store the electrical power generated by the generator. multiple first electric motors connected to the rotors to drive the same by the electric power supplied from the battery, a second electric motor connected to the gas turbine engine to motor the engine by the electric power supplied from the battery and a control unit to control flight, wherein the control unit stops supply of the fuel to the engine when a detected residual of the battery is equal to or greater than a predetermined value, and supplies electric power to the second electric motor to motor the engine when a detected temperature of the engine is equal to or higher than a predetermined temperature.