A vertical takeoff and landing aircraft using a hybrid electric propulsion system and a control method therefor according to an embodiment of the present invention: performs control such that, during vertical takeoff and landing of an aircraft (1), a generator (20), a power management device (4), and a battery management system (60) simultaneously provide power to a motor (80); and performs control such that, during a cruise flight or transition flight of the aircraft (1), the thrust of a second propeller (82) is increased and a battery (62) of the battery management system (60) is charged with redundant power generated by the generator (20).

Lift propulsion and stabilizing system and procedure for vertical takeoff and landing aircraft that consists in applying simultaneously and combined as lifters during the initial portion of the climb and at the end of the descent of: a) some fans or electric turbines, EDF, and b) at least one rotor with external blades and/or rotary and/or c) the engine flow directed downwards and/or d) pressure air jets injected on leading edges control fins, and/or e) water jets and/or f) supplemented with aerodynamic lift produced during frontal advance of the aircraft, the stabilization is achieved by the gyroscopic stiffness of the rotor and two or more lifting fans oscillating fins and/or air jets located on two or stabilizers more peripheral points in a plane perpendicular to the vertical axis of the aircraft.

A ground effect flight vehicle comprising, a fuselage (1), a wing assembly (4, 5), an engine assembly comprising one or more engines or engine sets (6, 7, 8), and a hull (2) for enabling floatation of the vehicle; wherein the wing assembly (4, 5) comprises stabilizer wings (4) and/or the one or more engines (6, 7, 8) are equipped to provide an airflow departing from the engines (6, 7, 8) which is positionable in one of multiple positions, a first position of the multiple positions which is arranged to generate lift for vertical take-off purpose, and a second position of the multiple positions which is for horizontal cruise flight.

An apparatus for facilitating propulsion of a vehicle. The apparatus comprises a housing with an interior space, an inlet, and an outlet, a propulsion mechanism, and a gimbal. The propulsion mechanism is disposed in the interior space and comprises and an upper rotor and a lower rotor rotatably mounted on a first portion and a second portion of a spindle. The upper rotor rotates in a first direction and the lower rotor rotates in a second direction opposite to the first direction. Upper rotor blades have a first blade pitch and lower rotor blades have a second blade pitch opposite to the first blade pitch. The rotating of the upper rotor and the lower rotor crates a fluid flow from the inlet to the outlet for generating a directional thrust. The gimbal rotatably attaches the propulsion mechanism to the housing. The housing is rotatable for vectoring the directional thrust.

A flying device includes a main body, to which a combustion engine, an electric motor, an electricity generator and an electrical energy transfer circuit are attached. The combustion engine and electric motor are arranged to create thrust vectors and are placed on either side of the main body in order to create thrust vectors on each side of a plane of separation of said body. The electricity generator is mechanically coupled to the combustion engine in order to be driven thereby. The electrical energy transfer circuit is connected between the electricity generator and the electric motor, the energy transfer circuit being configured to create mechanical resistance that slows the combustion engine and to produce electrical energy in order to power the electric motor.

A flying device includes a main body, to which a combustion engine, an electric motor, an electricity generator and an electrical energy transfer circuit are attached. The combustion engine and electric motor are arranged to create thrust vectors and are placed on either side of the main body in order to create thrust vectors on each side of a plane of separation of said body. The electricity generator is mechanically coupled to the combustion engine in order to be driven thereby. The electrical energy transfer circuit is connected between the electricity generator and the electric motor, the energy transfer circuit being configured to create mechanical resistance that slows the combustion engine and to produce electrical energy in order to power the electric motor.

A thrust generator for a rotorcraft includes: a support part detachably mounted to a base provided in the rotorcraft; a rotor shaft rotatably supported by the support part; multiple rotating blades joined to the rotor shaft; and a drive unit detachably mounted to the support part or the base, wherein an output shaft of the drive unit is detachably connected to the rotor shaft.

The present invention provides an unmanned aerial vehicle (100) comprising: a flight system (4) for producing thrust to manoeuvre the unmanned aerial vehicle (100). The flight system (4) comprises: one or more flight rotors (42) defining a plane passing through each flight rotor and a thrust direction generally perpendicular to the plane; and one or more electric motor (44) for driving the one or more flight rotors (42). The unmanned aerial vehicle (100) further comprises: a cargo area for coupling to or receiving a load (200); and a load system (6) for providing thrust additional to the thrust provided by the flight system (4) to thereby lift a load attached to the connection point. The load system (6) comprises: a first gas turbine propulsion system; and a controller configured to control the flight system (4) and load system (6).