Distributed propulsion system for vertical take off and landing closed wing aircraft
An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.
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 having a rear section and a nose section, the fuselage at least partially disposed between the first wing segment and the second wing segment;
a first spoke and a second spoke coupling the fuselage to the first wing segment;
a third spoke and a fourth spoke coupling the fuselage to the second wing segment;
a motor disposed within each spoke in a distributed configuration; and
a propeller operably connected to each motor;
wherein the nose section of the fuselage extends above the propellers, a leading edge of the first wing segment and a leading edge of the second wing segment when the aircraft is in vertical takeoff and landing, and
wherein the nose section of the fuselage extends forward beyond the propellers, the leading edge of the first wing segment and the leading edge of the second wing segment when the aircraft is in forward flight.
2 . The aircraft of claim 1 , wherein the fuselage is configured to carry a payload.
3 . The aircraft of claim 1 , wherein the first and second wing segments, the fuselage, and the first, second, third and fourth spokes are not substantially reconfigured for transition between vertical takeoff and landing, stationary flight and forward flight.
4 . The aircraft of claim 1 , wherein the fuselage comprises two or more modules.
5 . The aircraft of claim 1 , wherein the aircraft is unmanned.
6 . The aircraft of claim 1 , wherein the each of the three or more propellers comprise a variable speed constant pitch propeller.
7 . The aircraft of claim 1 , wherein the first, second, third or fourth spokes are operable to change a position of the first or second wing segments with respect to the fuselage or vice versa.
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 having a rear section and a nose section, the fuselage at least partially disposed between the first wing segment and the second wing segment;
a first spoke and a second spoke coupling the fuselage to the first wing segment;
a third spoke and a fourth spoke coupling the fuselage to the second wing segment;
a motor disposed within each spoke;
a propeller proximate to a leading edge of each spoke and operably connected to the motor;
wherein the nose section of the fuselage extends above the propellers, a leading edge of the first wing segment and a leading edge of the second wing segment when the aircraft is in vertical takeoff and landing, and
wherein the nose section of the fuselage extends forward beyond the propellers, the leading edge of the first wing segment and the leading edge of the second wing segment when the aircraft is in forward flight.
9 . The aircraft of claim 8 , wherein the fuselage is configured to carry a payload.
10 . The aircraft of claim 8 , wherein the first and second wing segments, the fuselage, and the first, second, third and fourth spokes are not substantially reconfigured for transition between vertical takeoff and landing, stationary flight and forward flight.
11 . The aircraft of claim 8 , wherein the fuselage comprises two or more modules.
12 . The aircraft of claim 8 , wherein the aircraft is unmanned.
13 . The aircraft of claim 8 , wherein the propeller is a variable speed constant pitch propeller.
14 . An aircraft capable of vertical takeoff and landing, stationary flight and forward flight, the aircraft comprising:
a fuselage having a rear section and a nose section, the fuselage at least partially disposed between a first wing segment and a second wing segment;
a first spoke and a second spoke coupling the fuselage to the first wing segment;
a third spoke and a fourth spoke coupling the fuselage to the second wing segment;
one or more motors disposed within each spoke; and
a propeller proximate to a leading edge of each spoke, and operably connected to the one or more motors;
wherein the nose section of the fuselage extends above the propellers, a leading edge of the first wing segment and a leading edge of the second wing segment when the aircraft is in vertical takeoff and landing, and
wherein the nose section of the fuselage extends forward beyond the propellers, the leading edge of the first wing segment and the leading edge of the second wing segment when the aircraft is in forward flight.
15 . The aircraft of claim 14 , wherein the fuselage is configured to carry a payload.
16 . The aircraft of claim 14 , wherein the first and second wing segments, the fuselage, and the first, second, third and fourth spokes are not substantially reconfigured for transition between vertical takeoff and landing, stationary flight and forward flight.
17 . The aircraft of claim 14 , wherein the fuselage comprises two or more modules.
18 . The aircraft of claim 14 , wherein the aircraft is unmanned.
19 . The aircraft of claim 14 , wherein the propeller is a variable speed constant pitch propeller.
20 . The aircraft of claim 14 , wherein the first, second, third and fourth spokes are operable to change a position of the first or second wing segments with respect to the fuselage or vice versa.