Distributed propulsion system
The present invention includes a distributed propulsion system for a craft that comprises a frame, a plurality of hydraulic or electric motors disposed within or attached to the frame in a distributed configuration; a propeller operably connected to each of the hydraulic or electric motors, a source of hydraulic or electric power disposed within or attached to the frame and coupled to each of the disposed within or attached to the frame, wherein the source of hydraulic or electric power provides sufficient energy density for the craft to attain and maintain operations of the craft, a controller coupled to each of the hydraulic or electric motors, and one or more processors communicably coupled to each controller that control an operation and speed of the plurality of hydraulic or electric motors.
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 propeller operably connected to each of 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 the propeller is configured to provide lift when the aircraft is in vertical takeoff and landing and stationary flight,
wherein the propeller is configured to provide thrust in when the aircraft is in forward flight;
wherein the fuselage extends above the propellers, a leading edge of the first wing segment and the second wing segment when the aircraft is landed; and
wherein the fuselage extends forward beyond the propellers, a leading edge of the first wing segment and the second wing segment when the aircraft is 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 propeller is a variable speed constant pitch propeller.
7. The aircraft of claim 1 , wherein each of the plurality of electric motors is operably connected to three propellers.
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;
a plurality of electric motors attached to the plurality of spokes in a distributed configuration, each electric motor comprising:
a propeller operably connected to the electric motor;
a source of power coupled to the electric motor; and
a controller coupled to the source of power and connected to the electric motor;
wherein the propeller is configured to provide lift when the aircraft is in vertical takeoff and landing and stationary flight,
wherein the propeller is configured to provide thrust in when the aircraft is in forward flight;
wherein the fuselage extends above the propellers, a leading edge of the first wing segment and the second wing segment when the aircraft is landed; and
wherein the fuselage extends forward beyond the propellers, a leading edge of the first wing segment and the second wing segment when the aircraft is 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 propeller is a variable speed constant pitch propeller.
14. The aircraft of claim 8 , wherein each of the plurality of electric motors is operably connected to three propellers.
15. An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, the aircraft comprising:
a frame comprising a fuselage, a first wing segment and a second wing segment;
a plurality of electric motors attached to the frame in a distributed configuration;
a propeller operably connected to each of 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 the propeller is configured to provide lift when the aircraft is in vertical takeoff and landing and stationary flight,
wherein the propeller is configured to provide thrust in when the aircraft is in forward flight;
wherein the fuselage extends above the propellers, a leading edge of the first wing segment and the second wing segment when the aircraft is landed, and
wherein the fuselage extends forward beyond the propellers, a leading edge of the first wing segment and the second wing segment when the aircraft is 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 electric motors comprises six electric motors.
19. The aircraft of claim 15 , wherein the propeller is a variable speed constant pitch propeller.
20. The aircraft of claim 15 , wherein each of the plurality of electric motors is operably connected to three propellers.