# US 10,480,455 B2 · Cryogenic circuit conditioning system > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 10,480,455 B2 - Document ID: US10480455B2 - Status: Granted - Kind: B2 - Application number: 14/762,239 - Filed: 2014-01-21 - Published: 2015-12-03 - Granted: 2019-11-19 - Earliest claimed: 2013-01-22 - Assignees: Arianegroup SAS - Applicants: Airbus Defence and Space SAS - Inventors: Jean-Phillipe Dutheil; Marie-Sophie Hameury - Web page: https://patentgrep.com/patent/US10480455B2 ## CPC - F02K 9/60: Constructional parts; Details not otherwise provided for - B64G 1/401: {Liquid propellant rocket engines (Ion or plasma engines B64G1/413; Arcjets and other resistojets B64G1/415)} - B64G 1/402: {Propellant tanks; Feeding propellants} - F02K 9/78: with an air-breathing jet-propulsion plant (with a ram-jet engine F02K7/18) - F25D 21/04: Preventing the formation of frost or condensate - F05D 2260/608: Aeration, ventilation, dehumidification or moisture removal of closed spaces - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR - F25D: REFRIGERATORS; COLD ROOMS; ICE-BOXES; COOLING OR FREEZING APPARATUS NOT OTHERWISE PROVIDED FOR (refrigerated showcases A47F3/04; thermally-insulated vessels for domestic use A47J41/00; refrigerated vehicles, see the appropriate subclasses of classes B60 - B64; containers with thermal insulation in general B65D81/38; heat-transfer, heat-exchange or heat-storage materials, e.g. refrigerants, or materials for the production of heat or cold by chemical reactions other than by combustion C09K5/00; thermally-insulated vessels for liquefied or solidified gases F17C; air-conditioning or air-humidification F24F; refrigeration machines, plants, or systems F25B; cooling of instruments or comparable apparatus without refrigeration G12B) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract The subject of the invention is a device for the in-flight conditioning of equipment of cryogenic circuits of an aircraft, which device includes means for bleeding air from outside the aircraft, means for extracting nitrogen from this air using a nitrogen separator of the OBIGGS type and means for distributing this nitrogen around the equipment. The device notably includes means for distributing nitrogen around the various pieces of equipment of cryogenic circuits using a system of piping provided with calibrated orifices. ## Claims ### Claim 1 A device that is configured for in-flight conditioning of cryogenic circuits equipment of an aerospace vehicle, which distributes cryogenic fluids from at least one tank to an engine of the aerospace vehicle, the device comprising: means for bleeding air from outside of the aerospace vehicle during an atmospheric part of a flight comprising an intake that is configured to bleed air from a compressor of a turbine engine of the aerospace vehicle; means for extracting nitrogen from the air using a nitrogen separator of the OBIGGS type; means for distributing the nitrogen that is configured to surroundingly interface the nitrogen with the cryogenic circuits equipment, comprising a circuit of pipework having orifices that are disposed along said pipework and are calibrated to keep the cryogenic circuits equipment conditioned at an overpressure with respect to surrounds thereof, said orifices being located around the cryogenic circuits equipment and effecting a nitrogen gas sweep of the cryogenic circuits equipment with nitrogen; and drying mean located downstream of the nitrogen separator that include a discharge that is configured to dispense water to an exterior of the aerospace vehicle. ### Claim 2 (depends on 1) The device of claim 1, wherein said means for distributing the nitrogen comprise pressure-boosting means that include a compressor. ### Claim 3 (depends on 1) The device of claim 1, further comprising means that are configured to encapsulate the cryogenic circuits equipment that are at least one of casings and sleeves. ### Claim 4 (depends on 1) The device of claim 1, wherein the device is configured to distribute the nitrogen around the cryogenic circuits equipment that distribute the cryogenic fluids at least during a phase of the atmospheric part of the flight of the aerospace vehicle. ### Claim 5 (depends on 1) The device of claim 1, wherein the air intake directly draws in air from the outside the aerospace vehicle. ### Claim 6 (depends on 1) The device of claim 1, wherein the device supplements a conditioning circuit that is external to the aircraft and connected to the aerospace vehicle and that is configured to circulate one of nitrogen and helium. ### Claim 7 An aircraft comprising: a rocket motor using at least one cryogenic propellant fluid; and device that is configured for in-flight conditioning of cryogenic circuits equipment of the aircraft, which distributes cryogenic fluids from at least one tank to an engine of the aircraft and comprises an air intake that is configured to bleed air from a compressor of a turbine engine outside of the aircraft during an atmospheric part of a flight an on board inert gas generator system (OBIGGS) type nitrogen separator that is configured to extract nitrogen from the air; means for distributing the nitrogen that is configured to surroundingly interface the nitrogen with the cryogenic circuits equipment, t-comprising a circuit of pipework having orifices that are disposed along said pipework and are calibrated to keep the cryogenic circuits equipment conditioned at an overpressure with respect to surrounds thereof, said orifices being located around the cryogenic circuits equipment and effecting a nitrogen gas sweep of the cryogenic circuits equipment with nitrogen; and drying mean located downstream of the nitrogen separator that include a discharge that is configured to dispense water to an exterior of the aircraft. ### Claim 8 (depends on 7) The aircraft of claim 7, wherein said aircraft further comprises an aerobic turbine engine so that the aircraft has dual propulsion formed by the rocket motor and the aerobatic turbine engine. ### Claim 9 A method for conditioning cryogenic circuits equipment of an aerospace vehicle, the method comprising: connecting an external conditioning circuit on the ground to the aircraft and conditioning the cryogenic circuits equipment; and providing in-flight conditioning of said cryogenic circuits equipment using an device that is configured for in-flight conditioning of cryogenic circuits equipment of the aircraft, which distributes cryogenic fluids from at least one tank to an engine of the aerospace vehicle and comprises an air intake that is configured to bleed air from a compressor of a turbine engine outside of the aerospace vehicle during an atmospheric part of a flight an on board inert gas generator system (OBIGGS) type nitrogen separator that is configured to extract nitrogen from the air; means for distributing the nitrogen that is configured to surroundingly interface the nitrogen with the cryogenic circuits equipment, comprising a circuit of pipework having orifices that are disposed along said pipework and are calibrated to keep the cryogenic circuits equipment conditioned at an overpressure with respect to surrounds thereof, said orifices being located around the cryogenic circuits equipment and effecting a nitrogen gas sweep of the cryogenic circuits equipment with nitrogen; and drying mean located downstream of the nitrogen separator that include a discharge that is configured to dispense water to an exterior of the aerospace vehicle. ### Claim 10 An device that is configured for in-flight conditioning of cryogenic circuits equipment of an aerospace vehicle by distributing cryogenic fluids from at least one tank to an engine of said aerospace vehicle, the device comprising: an intake that is configured to bleed air from a compressor of a turbine engine of the aerospace vehicle; an on board inert gas generator system (OBIGGS) type nitrogen separator; a circuit of nitrogen distribution pipework that is equipped with orifices that are disposed along said pipework and calibrated to keep the cryogenic circuits equipment at an overpressure with respect to surroundings thereof, said orifices being located around the cryogenic equipment, said circuit of nitrogen distribution pipework carrying nitrogen at said calibrated orifices, said calibrated orifices effecting local nitrogen gas sweep of the cryogenic circuits equipment with nitrogen; and drying means located downstream of the nitrogen separator, said drying means including a discharge that is configured to dispense of water to an outside of the aerospace vehicle. ### Claim 11 (depends on 10) The device of claim 10, further comprising means for encapsulating the cryogenic circuits equipment that includes at least one of casings and sleeves. ### Claim 12 (depends on 10) The device of claim 10, wherein the device is configured to distribute conditioned nitrogen around the cryogenic circuits equipment that distribute the cryogenic fluids at least during a phase of atmospheric flight of the aerospace vehicle. ### Claim 13 (depends on 10) The device as claimed in claim 10, wherein the device supplements a ground device that is configured to condition circuits external to the aerospace vehicle by circulating one of nitrogen and helium. ### Claim 14 An aircraft, comprising: a rocket motor having at least one cryogenic propellant fluid; and wherein said aircraft is an aerospace vehicle that comprises a device that is configured for in-flight conditioning of cryogenic circuits equipment of the aircraft by distributing cryogenic fluids from at least one tank to an engine of said aircraft, the device comprising an intake that is configured to bleed air from a compressor of a turbine engine of the aircraft an on board inert gas generator system (OBIGGS) type nitrogen separator; a circuit of nitrogen distribution pipework that is equipped with orifices that are disposed along said pipework and calibrated to keep the cryogenic circuits equipment at an overpressure with respect to surroundings thereof, said orifices being located around the cryogenic equipment, said circuit of nitrogen distribution pipework carrying nitrogen at said calibrated orifices, said calibrated orifices effecting local nitrogen gas sweep of the cryogenic circuits equipment with nitrogen; and a discharge that is configured to dispense of water to an outside of the aerospace vehicle aircraft. ### Claim 15 (depends on 14) The aircraft of claim 14, further comprising an aerobic turbine engine so that said aircraft has dual propulsion formed by the rocket motor and the aerobic turbine engine. ### Claim 16 A method for conditioning cryogenic circuits equipment of an aerospace vehicle, the method comprising the following steps: conditioning the cryogenic circuits equipment of the aerospace vehicle on the ground using an external conditioning circuit connected to the aerospace vehicle; and performing in-flight conditioning of said cryogenic circuits equipment using a device that is configured for in-flight conditioning of cryogenic circuits equipment of the aerospace vehicle by distributing cryogenic fluids from at least one tank to an engine of said aerospace vehicle, the device comprising an intake that is configured to bleed air from a compressor of a turbine engine of the aerospace vehicle; an on board inert gas generator system (OBIGGS) type nitrogen separator; a circuit of nitrogen distribution pipework that is equipped with orifices that are disposed along said pipework and calibrated to keep the cryogenic circuits equipment at an overpressure with respect to surroundings thereof, said orifices being located around the cryogenic equipment, said circuit of nitrogen distribution pipework carrying nitrogen at said calibrated orifices, said calibrated orifices effecting local nitrogen gas sweep of the cryogenic circuits equipment with nitrogen; and a discharge that is configured to dispense of water to an outside of the aerospace vehicle aircraft.