Electric vertical take off and landing vehicle

An aircraft comprising:

• an airframe;
• a coaxial main rotor assembly including a static mast, and an upper rotor assembly and a lower rotor assembly rotatable about a main rotor axis defined by the static mast, wherein the upper rotor assembly and the lower rotor assembly are independently rotatable about the static mast;
• a propulsion system including:
• propulsion sources for directly driving at least one of the upper rotor assembly and the lower rotor assembly, wherein the propulsion sources comprise:
• a first propulsion source directly coupled to the upper rotor assembly, the first propulsion source being operable to rotate the upper rotor assembly about the main rotor axis in a first direction;
• and
• a second propulsion source directly coupled to the lower rotor assembly, the second propulsion source being independent from the first propulsion source and operable to rotate the lower rotor assembly about the main rotor axis in a second direction;
• and
• a flight control system operably coupled to the propulsion system, the flight control system being operable to independently control a rotational speed of the upper rotor assembly and the lower rotor assembly relative to the static mast, wherein the flight control system is operably coupled to the first propulsion source and the second propulsion source, wherein the flight control system is operable to control aircraft yaw via operation of the first propulsion source and the second propulsion source.