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 vertical takeoff and landing and stationary flight, and substantially in a direction of a forward flight in a forward flight mode.
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 the fuselage extends above the first wing segment, the second wing segment, the plurality of spokes, and the propellers when the aircraft is in vertical takeoff and landing and stationary flight, and
wherein the fuselage is forward of first wing segment, the second wing segment, the plurality of spokes, and the propellers when the aircraft is in 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 the fuselage extends above the first wing segment, the second wing segment, the plurality of spokes, and the propellers when the aircraft is in vertical takeoff and landing and stationary flight, and
wherein the fuselage is forward of the first wing segment, the second wing segment, the plurality of spokes, and the propellers when the aircraft is in 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 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 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 the fuselage extends above the plurality of wing segments and the propellers when the aircraft is in vertical takeoff and landing and stationary flight, and
wherein the fuselage is forward of the plurality of wing segments and the propellers when the aircraft is in 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.