# US 2025/0145271 A1 · Aircraft with Hybrid Power Supply and Unobstructed Cabin Door Access > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2025/0145271 A1 - Document ID: US20250145271A1 - Status: Published application - Kind: A1 - Application number: 18/934,165 - Filed: 2024-10-31 - Published: 2025-05-08 - Earliest claimed: 2023-11-02 - Assignees: Textron Aviation Inc. - Applicants: Textron Aviation Inc. - Inventors: Gonzalo Eduardo Mendoza; Corey Wailes Hagemeister; Steven Michael Klausmeyer - Web page: https://patentgrep.com/patent/US20250145271A1 ## CPC - B64C 1/1423: {Passenger doors} - B64D 27/31: within, or attached to, wings - B64D 27/33: Hybrid electric aircraft - B64D 31/18: for hybrid-electric power plants - B64D 27/355: using fuel cells - B64D 27/357: using batteries - B64D 2041/005: {Fuel cells} - 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 ## Abstract An aircraft having unobstructed cabin door access includes a hybrid power drive with a combustion engine connected to an electricity generating machine. Components of the hybrid power drive are positioned throughout the aircraft to provide a weight distribution having an aft bias. The aircraft further includes a forward swept wing and a cabin door positioned forward of the forward swept wing, such that access into a fuselage of the aircraft via the cabin door is unobstructed by the forward swept wing. ## Claims ### Claim 1 An aircraft having unobstructed cabin door access, the aircraft comprising: a hybrid power drive comprising a combustion engine connected to an electricity generating machine; a weight distribution of the hybrid power drive comprising an aft bias; a forward swept wing; and a cabin door positioned forward of the forward swept wing such that access into a fuselage of the aircraft via the cabin door is unobstructed by the forward swept wing. ### Claim 2 (depends on 1) The aircraft of claim 1 comprising a V-tail empennage. ### Claim 3 (depends on 1) The aircraft of claim 1, wherein components of the hybrid power drive comprise one or more engines, one or more generators, one or more batteries, and one or more electric motors. ### Claim 4 (depends on 1) The aircraft of claim 1, wherein components of the hybrid power drive comprise one or more batteries and one or more electric motors. ### Claim 5 (depends on 1) The aircraft of claim 1, wherein components of the hybrid power drive comprise one or more hydrogen fuel cell module(s). ### Claim 6 (depends on 3) The aircraft of claim 3, wherein the weight distribution of the hybrid power drive comprises: the engine(s), the generator(s), and the battery(ies) being located aft of passenger seats in an aft portion of the fuselage; and the electric motor(s) being located forward of pilot seats in a nose portion of the aircraft. ### Claim 7 (depends on 3) The aircraft of claim 3, wherein the weight distribution of the hybrid power drive comprises: the engine(s) and the generator(s) being located aft of passenger seats in an aft portion of the fuselage; and the electric motor(s) and the battery(ies) being located forward of pilot seats in a nose portion of the aircraft. ### Claim 8 (depends on 3) The aircraft of claim 3, wherein the weight distribution of the hybrid power drive comprises: the battery(ies) being located aft of passenger seats in an aft portion of the fuselage; and the engine(s), the generator(s), and the electric motor(s) being located forward of pilot seats in a nose portion of the aircraft. ### Claim 9 (depends on 4) The aircraft of claim 4, wherein the weight distribution of the electric power drive comprises: a battery located aft of passenger seats in an aft portion of the fuselage; and the electric motor(s) and additional batteries and power electronics located forward of pilot seats in a nose portion of the aircraft. ### Claim 10 (depends on 5) The aircraft of claim 5, wherein the weight distribution of the hydrogen fuel cell power drive comprises: a hydrogen fuel tank, power batteries, and hydrogen fuel cell modules located aft of passenger seats in an aft portion of the fuselage; and one or more electric motors and additional batteries or fuel cell modules and power electronics located forward of pilot seats in a nose portion of the aircraft. ### Claim 11 (depends on 1) The aircraft of claim 1 comprising an inlet disposed on a side of the fuselage. ### Claim 12 (depends on 1) The aircraft of claim 1 comprising an inlet disposed on an underside of the fuselage. ### Claim 13 (depends on 1) The aircraft of claim 1 comprising an inlet on top of the fuselage. ### Claim 14 (depends on 1) The aircraft of claim 1 comprising single or dual aft underbody exhaust arrangements for exhausting turbogenerator fumes. ### Claim 15 (depends on 1) The aircraft of claim 1 comprising single or dual aft underbody exhaust ports for releasing heat from a radiator. ### Claim 16 (depends on 1) The aircraft of claim 1 comprising an aft central outlet for exhausting one or more of a turbogenerator exhaust or a cooling radiator outflow. ### Claim 17 An aircraft having unobstructed cabin door access, the aircraft comprising: a hybrid power drive comprising one or more engines, one or more generators, one or more batteries, and one or more electric motors, wherein components of the hybrid power drive are positioned throughout the aircraft to provide a weight distribution having an aft bias; a forward swept wing; and a cabin door positioned forward of the forward swept wing such that access into a fuselage of the aircraft via the cabin door is unobstructed by the forward swept wing. ### Claim 18 (depends on 17) The aircraft of claim 17, wherein the weight distribution of the hybrid power drive comprises: the engine(s), the generator(s), and the battery(ies) being located aft of passenger seats in an aft portion of the fuselage; and the electric motor(s) being located forward of pilot seats in a nose portion of the aircraft. ### Claim 19 (depends on 17) The aircraft of claim 17, wherein the weight distribution of the hybrid power drive comprises: the engine(s) and the generator(s) being located aft of passenger seats in an aft portion of the fuselage; and the electric motor(s) and the battery(ies) being located forward of pilot seats in a nose portion of the aircraft. ### Claim 20 (depends on 17) The aircraft of claim 17, wherein the weight distribution of the hybrid power drive comprises: the battery(ies) being located aft of passenger seats in an aft portion of the fuselage; and the engine(s), the generator(s), and the electric motor(s) being located forward of pilot seats in a nose portion of the aircraft.