Distributed propulsion system for vertical take off and landing closed wing aircraft

An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, the aircraft comprising:

• a first wing segment and a second wing segment;
• a fuselage at least partially disposed between the first wing segment and the second wing segment;
• a plurality of spokes coupling the fuselage to the first wing segment and the second wing segment;
• and
• a plurality of electric motors attached to the plurality of spokes in a distributed configuration, each electric motor having:
• a propeller operably connected to the electric motor, a source of power coupled to the electric motor, and a processor coupled to the source of power and connected to the electric motor;
• wherein a longitudinal axis of the fuselage is substantially vertical in the vertical takeoff and landing and the stationary flight, and
• wherein the longitudinal axis of the fuselage is substantially in a direction of flight in the forward flight.

An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, the aircraft comprising:

• a plurality of wing segments;
• a fuselage at least partially disposed between the plurality of wing segments;
• a plurality of spokes coupling the fuselage to the plurality of wing segments;
• a plurality of electric motors attached to the plurality of spokes or wing segments in a distributed configuration;
• a plurality of propellers operably connected to the plurality of electric motors;
• a source of power coupled to each of the plurality of electric motors;
• and
• a plurality of controllers, each controller coupled to the source of power, and each controller connected to one of the plurality of electric motors;
• wherein a longitudinal axis of the fuselage is substantially vertical in the vertical takeoff and landing and the stationary flight, and
• wherein the longitudinal axis of the fuselage is substantially in a direction of flight in the forward flight.