# US 12,006,036 B2 · Distributed propulsion system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 12,006,036 B2 - Document ID: US12006036B2 - Status: Granted - Kind: B2 - Application number: 18/168,257 - Filed: 2023-02-13 - Published: 2023-06-22 - Granted: 2024-06-11 - Earliest claimed: 2016-05-13 - Assignees: Textron Innovations Inc. - Applicants: Textron Innovations Inc. - Inventors: Carlos Alexander Fenny; Rohn Lee Olson - Web page: https://patentgrep.com/patent/US12006036B2 ## CPC - B64C 11/28: Collapsible or foldable blades - B64C 1/068: {Fuselage sections} - B64C 3/10: Shape of wings - B64C 3/16: Frontal aspect - B64C 27/08: with two or more rotors - B64C 27/12: Rotor drives - B64C 27/50: Blades foldable to facilitate stowage of aircraft - B64C 29/0025: {the propellers being fixed relative to the fuselage} - B64C 29/02: having its flight directional axis vertical when grounded - B64C 39/024: {of the remote controlled vehicle type, i.e. RPV} - B64C 39/06: having disc- or ring-shaped wings - B64C 39/062: {having annular wings} - B64D 27/24: using steam or spring force (jet aircraft B64D27/16) - B64D 31/00: Power plant control systems; Arrangement of power plant control systems in aircraft - B64D 31/18: for hybrid-electric power plants - B64U 10/20: Vertical take-off and landing [VTOL] aircraft (flying platforms B64U10/13; helicopters B64U10/17) - B64U 30/293: Foldable or collapsible rotors or rotor supports - B64C 39/029: {Asymmetrical aircraft} - B64C 2001/0045: {Fuselages characterised by special shapes} - B64D 27/026: {comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine (Hybrid electric aircraft B64D27/33)} - B64U 30/10: Wings - B64U 50/11: using internal combustion piston engines - B64U 50/12: using turbine engines, e.g. turbojets or turbofans - B64U 50/19: using electrically powered motors - B64U 60/50: with landing legs - Y02T 50/10: Drag reduction - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - B64C: AEROPLANES; HELICOPTERS - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract 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. ## Claims ### Claim 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. ### Claim 2 (depends on 1) The aircraft of claim 1, wherein the aircraft is unmanned. ### Claim 3 (depends on 1) The aircraft of claim 1, wherein the source of power is a battery. ### Claim 4 (depends on 1) The aircraft of claim 1, wherein the first wing segment and the second wing segment form a closed wing. ### Claim 5 (depends on 1) The aircraft of claim 1, wherein the plurality of electric motors comprises six electric motors. ### Claim 6 (depends on 1) The aircraft of claim 1, wherein the propeller is a variable speed constant pitch propeller. ### Claim 7 (depends on 1) The aircraft of claim 1, wherein each of the plurality of electric motors is operably connected to three propellers. ### Claim 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. ### Claim 9 (depends on 8) The aircraft of claim 8, wherein the aircraft is unmanned. ### Claim 10 (depends on 8) The aircraft of claim 8, wherein the source of power is a battery. ### Claim 11 (depends on 8) The aircraft of claim 8, wherein the first wing segment and the second wing segment form a closed wing. ### Claim 12 (depends on 8) The aircraft of claim 8, wherein the plurality of electric motors comprises six electric motors. ### Claim 13 (depends on 8) The aircraft of claim 8, wherein the propeller is a variable speed constant pitch propeller. ### Claim 14 (depends on 8) The aircraft of claim 8, wherein each of the plurality of electric motors is operably connected to three propellers. ### Claim 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. ### Claim 16 (depends on 15) The aircraft of claim 15, wherein the aircraft is unmanned. ### Claim 17 (depends on 15) The aircraft of claim 15, wherein the source of power is a battery. ### Claim 18 (depends on 15) The aircraft of claim 15, wherein the plurality of electric motors comprises six electric motors. ### Claim 19 (depends on 15) The aircraft of claim 15, wherein the propeller is a variable speed constant pitch propeller. ### Claim 20 (depends on 15) The aircraft of claim 15, wherein each of the plurality of electric motors is operably connected to three propellers.