A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thnist to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

A compound rotor aircraft, comprises a fuselage, a lifting rotor, wings and thrust propellers, wherein the fuselage has a cabin for driving; the lifting rotor is configured to drive the fuselage to move in the vertical direction; a plurality of wings are provided and arranged symmetrically on the two sides of the fuselage; a plurality of thrust propellers are provided and arranged on the plurality of wings respectively, and are configured to provide horizontal thrust force to the fuselage to drive the aircraft to move in the horizontal direction. The aircraft has various flight modes such as helicopter mode, compound helicopter mode, gyrocopter mode, compound gyrocopter mode and fixed-wing cruising mode, and can be transited among the modes. In the case of power failure of the lifting rotor, the aircraft can be transited into a gyrocopter state and continue the flight safely.

An autogyro includes a frame and a rotor hub coupled to the frame. The autogyro also includes a connector coupled to the rotor hub and configured to couple the rotor hub to a ground-based pre-rotator device to rotate the rotor hub during a vertical take-off operation. The autogyro further includes a plurality of rotor blades coupled to the rotor hub, each rotor blade configured such that rotation of the rotor hub, during the vertical take-off operation, results in twisting the rotor blade from a first blade pitch distribution to a second blade pitch distribution.

A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thrust to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

A power apparatus including: a first engine (13) and a second engine (14) symmetrically arranged side by side; a first rotating shaft (21) connected to an output end of the first engine; a second rotating shaft (22) connected to an output end of the second engine; and a speed reducer (3) connected to the first rotating shaft and the second rotating shaft, where a side face of the first engine facing away from the second engine and a side face of the second engine facing away from the first engine are each provided with an exhaust port. Further provided is an unmanned helicopter including the power apparatus.

A compact, compound gyroplane employing torque compensated main rotor and hybrid power train is disclosed. The invention incorporates a torque-compensated main rotor system with a common Collective pitch control but no Cyclic function, which can be driven transiently during flight to allow vertical take-off, landing and hovering flight operations; torque compensation is via a coaxial counter-rotating (CACR) rotor system, or alternatively using one or more electronically-controlled, fixed-pitch, thruster motors. A mechanical or electro-mechanical hybrid power system allows a single engine to power vertical lift and forward propulsion; the use of electric motors for lift and torque compensation facilitates electronic (and potentially autonomous) control of critical phases of flight.

A multi-rotor aircraft includes a fuselage, a propulsion engine coupled to the fuselage that generates thnist to propel the aircraft along a first vector during forward flight, and rotors coupled to the fuselage, each rotor comprising blades, each rotor coupled to a motor, and each motor configured to supply power to and draw power from the coupled rotor. The aircraft includes a flight control system configured to control the motors coupled to the rotors in a power managed regime in which a net electrical power, consisting of a sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system. The flight control system can also be leveraged to adjust rotor control inputs to modify at least one of thrust, roll, pitch, or yaw of the multi-rotor aircraft.

An autogyro includes a fuselage with a rotor. The rotor includes rotor blades which are arranged on an upper face of the fuselage, and a rotor drive which temporarily drives the rotor via a first motor. The rotor blades autorotate via an airflow.