EVTOL aircraft using large, variable speed tilt rotors
AssigneeKarem Aircraft, Inc.
InventorsAbe Karem, William Martin Waide
Life of this patent
Estimating the term…
Abstract
Apparatus, systems, and methods are contemplated for electric powered vertical takeoff and landing (eVTOL) aircraft. Such are craft are engineered to carry safely carry at least 500 pounds (approx. 227 kg) using a few (e.g., 2-4) rotors, generally variable speed rigid (non-articulated) rotors. It is contemplated that one or more rotors generate a significant amount of lift (e.g., 70%) during rotorborne flight (e.g., vertical takeoff, hover, etc), and tilt to provide forward propulsion during wingborne flight. The rotors preferably employ individual blade control, and are battery powered. The vehicle preferably flies in an autopilot or pilotless mode and has a relatively small (e.g., less than 45′ diameter) footprint.
Claims36
An electric powered VTOL aircraft capable of carrying a payload of at least 500 pounds, comprising:
- a fuselage;
- a wing mechanically coupled to the fuselage;
- at least first and second primary variable speed rigid rotors configured to provide lift for the fuselage, wherein each of the first and second rotors is open, and not embedded in the wing;
- each of the first and second primary variable speed rotors driven at least by at least one electric motor, and the first and second primary variable speed rotors are sized and dimensioned to collectively provide at least 70% of lift on vertical takeoff;
- and
- at least one electric motor is powered by at least a first power source.
An electric powered VTOL aircraft capable of carry a payload of at least 500 pounds, comprising:
- a fuselage;
- a wing mechanically coupled to the fuselage, the wing sized and dimensioned to provide for wing loading no higher than 40 psf, and for wingborne stall speed no higher than 90 KIAS;
- at least first and second primary, variable speed, rigid rotors configured to provide lift for the fuselage, wherein each of the first and second rotors is open, and not embedded in the wing;
- each of the rotors having blades with individual blade control, and flap stiffness that is not less than the product of 200 times the rotor diameter in feet to the fourth power, as measured in lbs-in2, at 30% of the rotor radius as measured from a center of rotor rotation
- the first and second rotors driven at least by a least one electric motor, and sized and dimensioned to collectively provide at least 70% of lift on vertical takeoff;
- and
- the at least one electric motor is powered by at least a first power source.
Dependencies are inferred from the claim text.