Battery and engine architecture for VTOL aircraft

A method of operating an aircraft,

• wherein the aircraft is capable of vertical take-off and landing and capable of carrying a payload of at least 500 pounds, the aircraft having a fuselage, at least one wing mechanically coupled to the fuselage, a first nacelle mechanically coupled to the at least one wing on a first side of the fuselage and having a first static portion that is fixed with respect to the at least one wing and a first tilting portion that is tiltable with respect to the at least one wing, first and second electric motors mechanically coupled to the first tilting portion and configured to tilt with the first tilting portion, a first rotor mechanically coupled to the first tilting portion and configured to tilt with the first tilting portion, a first battery located in the at least one wing and configured to power the first electric motor, a second battery located in the first nacelle and configured to power the second electric motor, and wherein the first and second electric motors are configured to rotate the first rotor, the method comprising:
• in flight, rotating the first rotor by the first electric motor and the second electric motor,
• powering the first electric motor by the first battery;
• and
• powering the second electric motor by the second battery.

An aircraft, comprising:

• a fuselage;
• at least one wing mechanically coupled to the fuselage;
• a first nacelle mechanically coupled to the at least one wing on a first side of the fuselage and having a first static portion that is fixed with respect to the at least one wing and a first tilting portion that is tiltable with respect to the at least one wing;
• first and second stator windings mechanically coupled to the first tilting portion and configured to tilt with the first tilting portion;
• a first rotor mechanically coupled to the first tilting portion and configured to tilt with the first tilting portion, wherein the first and second stator windings are configured to rotate the first rotor;
• a first battery configured to power the first stator winding;
• and
• a second battery configured to power the second stator winding;
• wherein the first battery is located in the at least one wing and the second battery is located in the first nacelle;
• and
• wherein the aircraft is capable of vertical take-off and landing and carrying a payload of at least 500 pounds.