# US 10,501,193 B2 · Aircraft having a versatile propulsion system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,501,193 B2 - Document ID: US10501193B2 - Status: Granted - Kind: B2 - Application number: 15/606,242 - Filed: 2017-05-26 - Published: 2018-01-04 - Granted: 2019-12-10 - Earliest claimed: 2016-07-01 - Assignees: Textron Innovations Inc. - Applicants: Textron Innovations Inc. - Inventors: Paul K. Oldroyd; John Richard McCullough - Web page: https://patentgrep.com/patent/US10501193B2 ## CPC - B64U 30/10: Wings - B64C 11/46: Arrangements of, or constructional features peculiar to, multiple propellers {(B64C11/306 takes precedence)} - B64C 29/0033: {the propellers being tiltable relative to the fuselage} - B64C 29/02: having its flight directional axis vertical when grounded - B64D 27/06: within, or attached to, wings - B64D 27/12: within, or attached to, wings - B64D 31/00: Power plant control systems; Arrangement of power plant control systems in aircraft - B64U 10/20: Vertical take-off and landing [VTOL] aircraft (flying platforms B64U10/13; helicopters B64U10/17) - B64U 20/40: Modular UAVs - B64U 50/11: using internal combustion piston engines - B64U 50/19: using electrically powered motors - B64C 2211/00: Modular constructions of airplanes or helicopters - 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 70/60: Take-off or landing of UAVs from a runway using their own power - B64U 2101/61: for transporting passengers - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR - 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 - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract An aircraft having a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe and a versatile propulsion system attached to the airframe. The versatile propulsion system includes a plurality of propulsion assemblies. A flight control system is operable to independently control the propulsion assemblies. The propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode. In the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel. In the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source. ## Claims ### Claim 1 An aircraft having a vertical takeoff and landing fight mode and a forward flight mode, the aircraft comprising: an airframe; a versatile propulsion system attached to the airframe, the versatile propulsion system including a plurality of propulsion assemblies; and a flight control system operable to independently control the propulsion assemblies; wherein, the propulsion assemblies are interchangeably attachable to the airframe such that the aircraft has a liquid fuel flight mode and an electric flight mode; wherein, in the liquid fuel flight mode, energy is provided to each of the propulsion assemblies from a liquid fuel; and wherein, in the electric flight mode, energy is provided to each of the propulsion assemblies from an electric power source. ### Claim 2 (depends on 1) The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises: a nacelle operable to be coupled to the airframe; an engine disposed within the nacelle; a rotor hub mechanically coupled to the engine and operable to rotate responsive to operation of the engine; and a proprotor mechanically coupled to the rotor hub and operable to rotate therewith. ### Claim 3 (depends on 2) The aircraft as recited in claim 2 wherein each of the propulsion assemblies further comprises at least one liquid fuel tank disposed within the nacelle operable to contain the liquid fuel. ### Claim 4 (depends on 3) The aircraft as recited in claim 3 wherein each of the engines further comprises an internal combustion engine. ### Claim 5 (depends on 2) The aircraft as recited in claim 2 wherein each of the propulsion assemblies further comprises at least one battery disposed within the nacelle. ### Claim 6 (depends on 5) The aircraft as recited in claim 5 wherein each of the engines further comprises an electric motor. ### Claim 7 (depends on 1) The aircraft as recited in claim 1 further comprising a mixed flight mode wherein energy is provided to at least one of the propulsion assemblies from the liquid fuel and energy is provided to at least another of the propulsion assemblies from the electric power source. ### Claim 8 (depends on 1) The aircraft as recited in claim 1 further comprising a distributed power system. ### Claim 9 (depends on 1) The aircraft as recited in claim 1 further comprising a shared power system. ### Claim 10 (depends on 1) The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises a line replaceable unit. ### Claim 11 (depends on 1) The aircraft as recited in claim 1 wherein each of the propulsion assemblies further comprises an electronics node in communication with the flight control system, each of the electronics nodes operable to control operations of the respective propulsion assembly. ### Claim 12 (depends on 1) The aircraft as recited in claim 1 wherein the flight control system further comprises at least one of a redundant flight control system and a triply redundant flight control system. ### Claim 13 (depends on 1) The aircraft as recited in claim 1 wherein the flight control system commands operation of the propulsion assemblies responsive to at least one of onboard pilot flight control, remote flight control, autonomous flight control and combinations thereof. ### Claim 14 (depends on 1) The aircraft as recited in claim 1 further comprising a pod assembly selectively attachable to the airframe. ### Claim 15 (depends on 1) The aircraft as recited in claim 1 further comprising a passenger pod assembly rotatably attachable to the airframe such that the passenger pod assembly remains in a generally horizontal attitude in the vertical takeoff and landing fight mode, the forward flight mode and transitions therebetween. ### Claim 16 (depends on 1) The aircraft as recited in claim 1 wherein the airframe further comprises first and second wings; wherein, in the vertical takeoff and landing mode, the first wing is forward of the pod assembly and the second wing is aft of the pod assembly; and wherein, in the forward flight mode, the first wing is below the pod assembly and the second wing is above the pod assembly. ### Claim 17 (depends on 1) The aircraft as recited in claim 1 wherein the airframe further comprises first and second wings; wherein, in the vertical takeoff and landing mode, the first and second wings are above the pod assembly; and wherein, in the forward flight mode, the first wing is below the pod assembly and the second wing is above the pod assembly.