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 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 hybrid multi-rotor aircraft, includes a plurality of vertical propulsion rotors and at least one forward propulsion rotor. The aircraft also includes a rotor compartment within for each of the vertical propulsion rotors such that a vertical propulsion rotor may be stowed within its respective rotor compartment. A deployable rotor-compartment cover for each rotor compartment is provided and may be moved to an open state to allow the vertical propulsion rotors to be deployed and moved to a closed state to cover their respective vertical propulsion rotors when the vertical propulsion rotors or in a closed state.

The invention relates to a drive system for a vehicle, comprising at least one asymmetrical rotor (18), which has at least one rotor blade (20) extending radially from a rotor axle, and a counterweight (22) which is opposite the rotor axle, the system further comprising a control device for the electric motor (24), which connects the electric motor (24) to a battery for the power supply thereof, and is configured and designed, during a revolution cycle, which includes 1-3 revolutions of the rigid rotor blade (20), to bring about at least one acceleration phase, in which the electric motor (24) can be accelerated to accelerate the rotor (18), and at least one braking phase, in which the electric motor (24) can be braked, the control device being designed, during at least part of the braking phase, to connect the electric motor (24) to at least one battery element (28) in generator mode.

A rotor hub assembly includes an open rotor hub assembly with an open rotor hub and a mounting plate. The open rotor hub includes an annular base portion with periphery and a plurality of rotary member portions arranged about the annular base portion that each define an aperture for receiving a rotor blade. The mounting plate spans the annular base portion and is coupled to the annular base portion by a resilient member to accommodate radially expansion and contraction of the annular base portion according to loads exerted on the rotor hub by rotor blades seated in the apertures of the rotary member portions.

The present invention comprises a novel propulsion method and apparatus for personal air vehicles generally consisting of gyroscopic movable assembly containing a gyroscope flywheel that produces thrust. In a preferred embodiment the gyroscope is hubless. The gyroscope flywheel integrates permanent magnets along its perimeter ring while spokes with an airfoil cross-section and positive incidence angle create airflow when rotated. The spokes couple the gyroscope's perimeter ring with a smaller central hubless ring. Proximate to the gyroscope's flywheel is an electromagnet fixed assembly that produces phasing electromagnetic fields that rotate the gyroscopic movable assembly. The invention comprises a self-contained apparatus with no external motor because the assembly is a motor with a self-stabilizing gyroscope that produces directional airflow that can be used to propel air, land and sea vehicles.

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 rotor hub assembly includes an open rotor hub assembly with an open rotor hub and a mounting plate. The open rotor hub includes an annular base portion with periphery and a plurality of rotary member portions arranged about the annular base portion that each define an aperture for receiving a rotor blade. The mounting plate spans the annular base portion and is coupled to the annular base portion by a resilient member to accommodate radially expansion and contraction of the annular base portion according to loads exerted on the rotor hub by rotor blades seated in the apertures of the rotary member portions.