Distributed Propulsion System for Vertical Take Off and Landing Closed Wing Aircraft
An aircraft includes a closed wing, a fuselage at least partially disposed within a perimeter of the closed wing, and one or more spokes coupling the closed wing to the fuselage. A source of electric power is disposed within or attached to the closed wing, fuselage or one or more spokes. A plurality of electric motors are disposed within or attached to the one or more spokes in a distributed configuration. Each electric motor is connected to the source of electric power. A propeller is operably connected to each of the electric motors and proximate to a leading edge of the one or more spokes. One or more processors are communicably coupled to the plurality of electric motors. A longitudinal axis of the fuselage is substantially vertical in the vertical takeoff and landing and the stationary flight, and substantially in a direction of flight in the forward flight.
1 . 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;
a plurality of electric motors attached to the plurality of spokes 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 processor coupled to 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.
2 . The aircraft of claim 1 , wherein the aircraft is unmanned.
3 . The aircraft of claim 1 , wherein the source of power is a battery.
4 . The aircraft of claim 1 , wherein the first wing segment and the second wing segment form a closed wing.
5 . The aircraft of claim 1 , wherein the plurality of electric motors comprises six electric motors.
6 . The aircraft of claim 1 , wherein the propellers are variable speed constant pitch propellers.
7 . The aircraft of claim 1 , wherein three or more of the plurality of propellers are operably connected to one or more of the plurality of motors.
8 . 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.
9 . The aircraft of claim 8 , wherein the aircraft is unmanned.
10 . The aircraft of claim 8 , wherein the source of power is a battery.
11 . The aircraft of claim 8 , wherein the first wing segment and the second wing segment form a closed wing.
12 . The aircraft of claim 8 , wherein the plurality of electric motors comprises six electric motors.
13 . The aircraft of claim 8 , wherein the propellers are variable speed constant pitch propellers.
14 . The aircraft of claim 8 , wherein three or more of the plurality of propellers are operably connected to one or more of the plurality of motors.
15 . 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 within a perimeter of the plurality of wing segments;
a plurality of spokes coupling the fuselage to the plurality of wing segments;
a plurality of motors attached to the plurality of spokes or wing segments in a distributed configuration;
a plurality of propellers operably connected to the plurality of motors;
a source of power coupled to each of the plurality of motors; and
a plurality of controllers, each controller coupled to the source of power, and each controller connected to one of the plurality of 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.
16 . The aircraft of claim 15 , wherein the aircraft is unmanned.
17 . The aircraft of claim 15 , wherein the source of power is a battery.
18 . The aircraft of claim 15 , wherein the plurality of motors comprises six motors.
19 . The aircraft of claim 15 , wherein the propellers are variable speed constant pitch propellers.
20 . The aircraft of claim 15 , wherein three or more of the plurality of propellers are operably connected to one or more of the plurality of motors.