# US 11,878,798 B2 · Blended wing body aircraft with a fuel cell and method of use > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,878,798 B2 - Document ID: US11878798B2 - Status: Granted - Kind: B2 - Application number: 17/478,724 - Filed: 2021-09-17 - Published: 2023-03-23 - Granted: 2024-01-23 - Earliest claimed: 2021-09-17 - Assignees: JetZero, Inc. - Applicants: Jetzero, Inc. - Inventors: Shailesh Atreya; Ronald Tatsuji Kawai - Web page: https://patentgrep.com/patent/US11878798B2 ## CPC - B64D 37/30: Fuel systems for specific fuels - B64C 39/10: All-wing aircraft - B64D 27/33: Hybrid electric aircraft - B64D 27/355: using fuel cells - B64D 31/18: for hybrid-electric power plants - B64D 35/023: of series-parallel type - B64D 37/04: Arrangement thereof in or on aircraft - B64C 2039/105: {of blended wing body type} - B64D 2041/005: {Fuel cells} - B64D 2221/00: Electric power distribution systems onboard aircraft - Y02T 90/40: Application of hydrogen technology to transportation, e.g. using fuel cells - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - B64C: AEROPLANES; HELICOPTERS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract Certain aspects relate to a blended wing body aircraft with a fuel cell and methods of use. An exemplary aircraft includes a blended wing body, at least a propulsor mechanically affixed to the aircraft and configured to propel the aircraft, at least a first fuel store configured to store a first fuel, and at least a fuel cell configured to combine the first fuel with oxygen to produce electricity. ## Claims ### Claim 1 A blended wing body aircraft with a fuel cell, the aircraft comprising: a blended wing body aircraft; at least a first fuel store located within a transitional portion of the blended wing body aircraft and configured to store a first fuel, wherein the at least a first fuel store comprises a fuel environment mitigation configured to regulate the temperature and pressure of the first fuel, wherein the fuel environment mitigation comprises an insulation, wherein the insulation comprises a vacuum chamber disposed between an inner wall of the at least a first fuel store and an outer wall of the at least a first fuel store, and a pressure vessel wherein the pressure vessel is further configured to control fuel pressure; at least a fuel cell configured to combine the first fuel with oxygen to produce electricity; at least a second fuel store located within the blended wing body aircraft and configured to store a second fuel wherein the at least a second fuel store comprises a second environment mitigation configured to regulate the temperature and pressure of the second fuel, wherein the second fuel environment mitigation comprises a second insulation, wherein the second insulation comprises a second vacuum chamber disposed between an inner wall of the at least a second fuel store and an outer wall of the at least a second fuel store, and a second pressure vessel wherein the second pressure vessel is further configured to control a second fuel pressure; an auxiliary power system operatively connected with the at least a fuel cell, wherein the at least a fuel cell is configured to power the auxiliary power system, wherein the auxiliary power system is configured to power an anti-ice system and a braking system while in flight; at least a propulsor mechanically affixed to an upper aft surface of the blended wing body aircraft and configured to propel the blended wing body aircraft; and at least a nacelle configured to encapsulate the at least a propulsor. ### Claim 2 (depends on 1) The aircraft of claim 1, wherein the first fuel comprises one or more of liquid hydrogen and natural gas. ### Claim 3 (depends on 1) The aircraft of claim 1, wherein the second fuel comprises one or more of a kerosene based fuel and a gasoline based fuel. ### Claim 4 (depends on 1) The aircraft of claim 1, wherein the at least a propulsor comprises at least a combustion engine that burns the second fuel and produces mechanical work which is used to power the at least a propulsor. ### Claim 5 (depends on 1) The aircraft of claim 1, wherein the at least a propulsor comprises at least an electric motor operatively connected with the at least a fuel cell, and wherein the at least a fuel cell is configured to power the at least an electric motor. ### Claim 6 (depends on 1) The aircraft of claim 1, wherein the at least a propulsor comprises: at least a combustion engine that burns the second fuel and produces mechanical work which is used to power the at least a propulsor; and at least an electric motor operatively connected with the at least a fuel cell; and wherein the at least a fuel cell is configured to power the at least an electric motor. ### Claim 7 (depends on 1) The aircraft of claim 1, wherein the auxiliary power system is configured to power one or more of an avionic system, a flight control system, an environmental control system, a lighting system, a fuel system, a braking system, and a landing gear system. ### Claim 8 (depends on 1) The aircraft of claim 1, wherein the at least a propulsor comprises a combustion engine and the auxiliary power system is further configured to start the internal combustion engine. ### Claim 9 (depends on 1) The aircraft of claim 1, wherein the at least a second fuel store is located within a wing portion of the blended wing body. ### Claim 10 A method of use of a blended wing body aircraft with a fuel cell, the method comprising: storing a first fuel, using at least a first fuel store located within a transitional portion of a blended wing body of the blended wing body aircraft, wherein the at least a first fuel store comprises a fuel environment mitigation configured to regulate the temperature and pressure of the first fuel, wherein the fuel environment mitigation comprises an insulation, wherein the insulation comprises a vacuum chamber disposed between an inner wall of the at least a first fuel store and an outer wall of the at least a first fuel store, and a pressure vessel wherein the pressure vessel is further configured to control fuel pressure; combining the first fuel with oxygen to produce electricity, using at least a fuel cell; storing a second fuel, using at least a second fuel store located within the blended wing body, wherein the at least a second fuel store comprises a second environment mitigation configured to regulate the temperature of the second fuel, wherein the second fuel environment mitigation comprises a second insulation, wherein the second insulation comprises a second vacuum chamber disposed between an inner wall of the at least a second fuel store and an outer wall of the at least a second fuel store, and a second pressure vessel wherein the second pressure vessel is further configured to control a second fuel pressure; powering, using the at least a fuel cell, an auxiliary power system operatively connected with the at least a fuel cell, wherein the auxiliary power system is configured to power an anti-ice system and a braking system while in flight; and propelling the blended wing body aircraft, using at least a propulsor mechanically affixed to an upper aft surface the blended wing body aircraft, wherein the at least a propulsor is encapsulated by at least a nacelle. ### Claim 11 (depends on 10) The method of claim 10, wherein the first fuel comprises one or more of liquid hydrogen and natural gas. ### Claim 12 (depends on 10) The method of claim 10, wherein the second fuel comprises one or more of a kerosene based fuel and a gasoline based fuel. ### Claim 13 (depends on 10) The method of claim 10, further comprising: burning, using at least a combustion engine of the at least a propulsor, the second fuel; and producing, using the at least a combustion engine, mechanical work which is used to power the at least a propulsor. ### Claim 14 (depends on 10) The method of claim 10, further comprising: powering, using the at least a fuel cell, at least an electric motor of the at least a propulsor, operatively connected with the at least a fuel cell. ### Claim 15 (depends on 10) The method of claim 10, further comprising: burning, using at least a combustion engine of the at least a propulsor, the second fuel; producing, using the at least a combustion engine, mechanical work which is used to power the at least a propulsor; and powering, using the at least a fuel cell, at least an electric motor of the at least a propulsor, operatively connected with the at least a fuel cell. ### Claim 16 (depends on 10) The method of claim 10, further comprising: powering, using the auxiliary power system, one or more of an avionic system, a flight control system, an environmental control system, a lighting system, a fuel system, a braking system, and a landing gear system. ### Claim 17 (depends on 10) The method of claim 10, further comprising: starting, using the auxiliary power unit, a combustion engine of the at least a propulsor. ### Claim 18 (depends on 10) The method of claim 10, wherein the at least a second fuel store is located within a wing portion of the blended wing body.