US 12,325,516 B2
Distributed propulsion system
Carlos Alexander Fenny, Fort Worth, TX (US); and Rohn Lee Olson, Hurst, TX (US)
Assigned to TEXTRON INNOVATIONS INC., Providence, RI (US)
Filed by TEXTRON INNOVATIONS INC., Providence, RI (US)
Filed on Apr. 30, 2024, as Appl. No. 18/650,650.
Application 18/650,650 is a continuation of application No. 18/168,257, filed on Feb. 13, 2023, granted, now 12,006,036.
Application 18/168,257 is a continuation of application No. 16/717,524, filed on Dec. 17, 2019, granted, now 11,603,203, issued on Mar. 14, 2023.
Application 16/717,524 is a continuation of application No. 15/593,458, filed on May 12, 2017, granted, now 10,556,680, issued on Feb. 11, 2020.
Claims priority of provisional application 62/336,290, filed on May 13, 2016.
Claims priority of provisional application 62/336,363, filed on May 13, 2016.
Claims priority of provisional application 62/336,432, filed on May 13, 2016.
Claims priority of provisional application 62/336,465, filed on May 13, 2016.
Claims priority of provisional application 62/336,420, filed on May 13, 2016.
Prior Publication US 2024/0278910 A1, Aug. 22, 2024
Int. Cl. B64C 29/02 (2006.01); B64C 1/00 (2006.01); B64C 1/06 (2006.01); B64C 3/10 (2006.01); B64C 3/16 (2006.01); B64C 11/28 (2006.01); B64C 27/50 (2006.01); B64C 39/06 (2006.01); B64D 31/00 (2006.01); B64U 10/20 (2023.01); B64U 30/10 (2023.01); B64U 30/293 (2023.01); B64U 50/19 (2023.01); B64D 27/02 (2006.01); B64U 50/11 (2023.01); B64U 50/12 (2023.01); B64U 60/50 (2023.01)
CPC B64C 29/02 (2013.01) [B64C 1/068 (2013.01); B64C 3/10 (2013.01); B64C 3/16 (2013.01); B64C 11/28 (2013.01); B64C 27/50 (2013.01); B64C 39/06 (2013.01); B64C 39/062 (2013.01); B64D 31/00 (2013.01); B64U 10/20 (2023.01); B64U 30/293 (2023.01); B64C 2001/0045 (2013.01); B64D 27/026 (2024.01); B64U 30/10 (2023.01); B64U 50/11 (2023.01); B64U 50/12 (2023.01); B64U 50/19 (2023.01); B64U 60/50 (2023.01)] 20 Claims
OG exemplary drawing
 
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 plurality of spokes coupling the rear section of 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 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, a leading edge of the first wing segment and a leading edge of the second wing segment when the aircraft is in forward flight.